NACA 4424 (naca4424-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 4424 (naca4424-il) Reynolds number: 500,000 Max Cl/Cd: 64.34 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4424-il-500000.txt Download as CSV file: xf-naca4424-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4424
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -0.9929 0.08162 0.07687 -0.0903 1.0000 0.0764
-19.500 -0.9996 0.07886 0.07410 -0.0904 1.0000 0.0772
-19.250 -1.0070 0.07609 0.07130 -0.0904 1.0000 0.0780
-19.000 -1.0165 0.07300 0.06816 -0.0907 1.0000 0.0789
-18.750 -1.0104 0.06937 0.06444 -0.0942 0.9987 0.0801
-18.500 -1.0056 0.06575 0.06070 -0.0975 0.9970 0.0810
-18.250 -0.9977 0.06277 0.05769 -0.1003 0.9953 0.0824
-18.000 -0.9887 0.05995 0.05487 -0.1031 0.9936 0.0835
-17.750 -0.9801 0.05694 0.05181 -0.1062 0.9923 0.0848
-17.500 -0.9727 0.05409 0.04889 -0.1085 0.9901 0.0859
-17.250 -0.9658 0.05124 0.04596 -0.1107 0.9873 0.0872
-17.000 -0.9568 0.04853 0.04312 -0.1132 0.9849 0.0883
-16.750 -0.9475 0.04603 0.04066 -0.1154 0.9829 0.0900
-16.500 -0.9342 0.04368 0.03828 -0.1181 0.9813 0.0914
-16.250 -0.9180 0.04153 0.03607 -0.1208 0.9800 0.0929
-16.000 -0.9002 0.03950 0.03395 -0.1237 0.9790 0.0948
-15.750 -0.8966 0.03754 0.03191 -0.1233 0.9729 0.0959
-15.500 -0.8847 0.03548 0.02987 -0.1249 0.9701 0.0976
-15.250 -0.8669 0.03374 0.02811 -0.1270 0.9681 0.0994
-15.000 -0.8451 0.03220 0.02651 -0.1292 0.9667 0.1013
-14.750 -0.8206 0.03083 0.02505 -0.1316 0.9655 0.1032
-14.500 -0.8195 0.02932 0.02352 -0.1299 0.9578 0.1046
-14.250 -0.8012 0.02783 0.02204 -0.1312 0.9550 0.1068
-14.000 -0.7771 0.02664 0.02081 -0.1330 0.9533 0.1088
-13.750 -0.7492 0.02562 0.01972 -0.1349 0.9519 0.1113
-13.500 -0.7409 0.02449 0.01858 -0.1335 0.9452 0.1133
-13.250 -0.7220 0.02335 0.01744 -0.1340 0.9414 0.1155
-13.000 -0.6956 0.02240 0.01646 -0.1353 0.9392 0.1180
-12.750 -0.6664 0.02158 0.01558 -0.1368 0.9376 0.1205
-12.500 -0.6390 0.02054 0.01455 -0.1384 0.9361 0.1234
-12.250 -0.6274 0.01983 0.01384 -0.1366 0.9291 0.1256
-12.000 -0.6004 0.01919 0.01316 -0.1374 0.9252 0.1287
-11.750 -0.5688 0.01852 0.01244 -0.1390 0.9222 0.1317
-11.500 -0.5356 0.01775 0.01170 -0.1412 0.9197 0.1354
-11.250 -0.5062 0.01726 0.01118 -0.1423 0.9150 0.1389
-11.000 -0.4845 0.01688 0.01074 -0.1416 0.9076 0.1417
-10.750 -0.4513 0.01625 0.01014 -0.1437 0.9031 0.1460
-10.500 -0.4038 0.01581 0.00967 -0.1481 0.8999 0.1507
-10.250 -0.3908 0.01553 0.00934 -0.1456 0.8904 0.1536
-10.000 -0.3586 0.01507 0.00890 -0.1472 0.8838 0.1583
-9.750 -0.3122 0.01474 0.00851 -0.1513 0.8791 0.1634
-9.500 -0.3075 0.01452 0.00827 -0.1470 0.8685 0.1662
-9.250 -0.2805 0.01416 0.00792 -0.1473 0.8611 0.1709
-9.000 -0.2543 0.01396 0.00767 -0.1472 0.8536 0.1753
-8.750 -0.2436 0.01379 0.00745 -0.1439 0.8434 0.1786
-8.500 -0.2147 0.01346 0.00711 -0.1445 0.8358 0.1840
-8.250 -0.2108 0.01334 0.00698 -0.1397 0.8253 0.1875
-8.000 -0.1863 0.01321 0.00676 -0.1391 0.8168 0.1914
-7.750 -0.1779 0.01298 0.00655 -0.1353 0.8070 0.1962
-7.500 -0.1631 0.01283 0.00637 -0.1327 0.7974 0.2005
-7.250 -0.1459 0.01274 0.00621 -0.1305 0.7883 0.2051
-7.000 -0.1365 0.01260 0.00605 -0.1268 0.7784 0.2092
-6.750 -0.1201 0.01245 0.00587 -0.1245 0.7695 0.2143
-6.500 -0.1133 0.01238 0.00579 -0.1201 0.7595 0.2187
-6.000 -0.0935 0.01221 0.00555 -0.1126 0.7401 0.2276
-5.750 -0.0825 0.01214 0.00544 -0.1091 0.7308 0.2326
-5.500 -0.0752 0.01212 0.00538 -0.1047 0.7217 0.2372
-5.250 -0.0675 0.01206 0.00527 -0.1004 0.7118 0.2416
-5.000 -0.0582 0.01196 0.00517 -0.0965 0.7029 0.2472
-4.750 -0.0525 0.01190 0.00510 -0.0918 0.6933 0.2521
-4.500 -0.0351 0.01191 0.00500 -0.0895 0.6844 0.2573
-4.250 -0.0294 0.01179 0.00493 -0.0848 0.6758 0.2631
-4.000 -0.0176 0.01174 0.00486 -0.0814 0.6667 0.2693
-3.750 -0.0031 0.01174 0.00480 -0.0785 0.6582 0.2751
-3.500 0.0081 0.01168 0.00475 -0.0749 0.6495 0.2816
-3.250 0.0227 0.01165 0.00469 -0.0721 0.6413 0.2884
-3.000 0.0356 0.01164 0.00467 -0.0689 0.6334 0.2947
-2.750 0.0489 0.01162 0.00463 -0.0657 0.6253 0.3018
-2.500 0.0652 0.01161 0.00460 -0.0633 0.6175 0.3097
-2.250 0.0795 0.01161 0.00461 -0.0604 0.6104 0.3170
-2.000 0.0944 0.01158 0.00458 -0.0576 0.6031 0.3249
-1.750 0.1121 0.01160 0.00456 -0.0554 0.5958 0.3335
-1.500 0.1267 0.01161 0.00459 -0.0526 0.5893 0.3410
-1.250 0.1412 0.01157 0.00458 -0.0498 0.5825 0.3507
-1.000 0.1593 0.01161 0.00459 -0.0477 0.5760 0.3606
-0.750 0.1758 0.01161 0.00461 -0.0453 0.5700 0.3704
-0.500 0.1920 0.01159 0.00464 -0.0429 0.5640 0.3817
-0.250 0.2092 0.01163 0.00466 -0.0407 0.5577 0.3924
0.000 0.2280 0.01165 0.00469 -0.0388 0.5518 0.4063
0.250 0.2432 0.01164 0.00475 -0.0362 0.5467 0.4194
0.500 0.2592 0.01164 0.00479 -0.0338 0.5408 0.4353
0.750 0.2763 0.01165 0.00483 -0.0316 0.5353 0.4535
1.000 0.2959 0.01167 0.00490 -0.0299 0.5300 0.4745
1.250 0.3104 0.01165 0.00500 -0.0272 0.5251 0.4971
1.500 0.3259 0.01165 0.00509 -0.0247 0.5201 0.5239
1.750 0.3421 0.01167 0.00517 -0.0223 0.5146 0.5507
2.000 0.3622 0.01173 0.00527 -0.0208 0.5092 0.5788
2.250 0.3770 0.01173 0.00540 -0.0182 0.5048 0.6050
2.500 0.3932 0.01176 0.00553 -0.0159 0.4999 0.6318
2.750 0.4106 0.01181 0.00565 -0.0138 0.4948 0.6586
3.000 0.4316 0.01188 0.00577 -0.0125 0.4896 0.6888
3.250 0.4500 0.01191 0.00595 -0.0107 0.4852 0.7207
3.500 0.4701 0.01194 0.00612 -0.0093 0.4801 0.7547
3.750 0.4979 0.01198 0.00631 -0.0095 0.4748 0.7971
4.000 0.5462 0.01209 0.00651 -0.0139 0.4685 0.8434
4.250 0.6278 0.01228 0.00687 -0.0255 0.4624 0.8861
4.500 0.7063 0.01264 0.00728 -0.0363 0.4554 0.9110
4.750 0.7668 0.01313 0.00771 -0.0433 0.4486 0.9279
5.000 0.8070 0.01353 0.00813 -0.0460 0.4433 0.9428
5.250 0.8332 0.01391 0.00852 -0.0460 0.4377 0.9606
5.500 0.8642 0.01434 0.00890 -0.0470 0.4323 0.9729
5.750 0.8986 0.01478 0.00928 -0.0487 0.4266 0.9805
6.000 0.9355 0.01514 0.00967 -0.0510 0.4209 0.9865
6.250 0.9711 0.01560 0.01009 -0.0531 0.4146 0.9920
6.500 1.0099 0.01601 0.01042 -0.0560 0.4084 0.9963
6.750 1.0494 0.01631 0.01077 -0.0589 0.4029 0.9995
7.000 1.0625 0.01661 0.01105 -0.0568 0.3975 1.0000
7.250 1.0695 0.01695 0.01134 -0.0535 0.3925 1.0000
7.500 1.0786 0.01731 0.01168 -0.0506 0.3874 1.0000
7.750 1.0894 0.01765 0.01203 -0.0480 0.3825 1.0000
8.000 1.0998 0.01804 0.01241 -0.0454 0.3773 1.0000
8.250 1.1089 0.01854 0.01285 -0.0426 0.3721 1.0000
8.500 1.1209 0.01896 0.01330 -0.0404 0.3673 1.0000
8.750 1.1326 0.01942 0.01376 -0.0381 0.3616 1.0000
9.000 1.1423 0.01999 0.01430 -0.0357 0.3563 1.0000
9.250 1.1524 0.02058 0.01488 -0.0334 0.3508 1.0000
9.500 1.1650 0.02111 0.01542 -0.0315 0.3453 1.0000
9.750 1.1735 0.02182 0.01611 -0.0291 0.3393 1.0000
10.000 1.1832 0.02253 0.01680 -0.0269 0.3338 1.0000
10.250 1.1957 0.02315 0.01745 -0.0252 0.3284 1.0000
10.500 1.2042 0.02398 0.01825 -0.0231 0.3225 1.0000
10.750 1.2128 0.02483 0.01908 -0.0210 0.3169 1.0000
11.000 1.2242 0.02560 0.01989 -0.0194 0.3114 1.0000
11.250 1.2321 0.02657 0.02084 -0.0174 0.3052 1.0000
11.500 1.2396 0.02760 0.02185 -0.0155 0.2998 1.0000
11.750 1.2503 0.02851 0.02279 -0.0141 0.2940 1.0000
12.000 1.2565 0.02969 0.02395 -0.0122 0.2878 1.0000
12.250 1.2639 0.03085 0.02511 -0.0106 0.2823 1.0000
12.500 1.2730 0.03194 0.02623 -0.0092 0.2764 1.0000
12.750 1.2770 0.03339 0.02764 -0.0074 0.2705 1.0000
13.000 1.2852 0.03460 0.02888 -0.0061 0.2652 1.0000
13.250 1.2913 0.03601 0.03031 -0.0048 0.2593 1.0000
13.500 1.2940 0.03766 0.03192 -0.0032 0.2536 1.0000
13.750 1.3018 0.03902 0.03333 -0.0021 0.2487 1.0000
14.000 1.3068 0.04060 0.03491 -0.0009 0.2428 1.0000
14.250 1.3070 0.04256 0.03685 0.0005 0.2375 1.0000
14.500 1.3153 0.04398 0.03833 0.0013 0.2326 1.0000
14.750 1.3172 0.04593 0.04028 0.0024 0.2272 1.0000
15.000 1.3186 0.04790 0.04223 0.0035 0.2224 1.0000
15.250 1.3238 0.04966 0.04405 0.0042 0.2176 1.0000
15.500 1.3249 0.05177 0.04615 0.0051 0.2123 1.0000
15.750 1.3248 0.05402 0.04840 0.0060 0.2077 1.0000
16.000 1.3300 0.05585 0.05028 0.0065 0.2032 1.0000
16.250 1.3286 0.05830 0.05274 0.0072 0.1983 1.0000
16.500 1.3293 0.06055 0.05499 0.0079 0.1939 1.0000
16.750 1.3311 0.06279 0.05729 0.0083 0.1893 1.0000
17.000 1.3308 0.06522 0.05971 0.0088 0.1849 1.0000
17.250 1.3292 0.06781 0.06232 0.0092 0.1808 1.0000
17.500 1.3320 0.07003 0.06458 0.0094 0.1766 1.0000
17.750 1.3288 0.07284 0.06740 0.0097 0.1723 1.0000
18.000 1.3280 0.07540 0.06997 0.0099 0.1684 1.0000
18.250 1.3289 0.07789 0.07252 0.0100 0.1643 1.0000
18.500 1.3270 0.08066 0.07529 0.0100 0.1605 1.0000
18.750 1.3253 0.08339 0.07802 0.0101 0.1569 1.0000
19.000 1.3251 0.08607 0.08078 0.0100 0.1530 1.0000
19.250 1.3232 0.08888 0.08359 0.0098 0.1492 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 4424 (naca4424-il)