NACA 4424 (naca4424-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 4424 (naca4424-il) Reynolds number: 500,000 Max Cl/Cd: 55.58 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4424-il-500000-n5.txt Download as CSV file: xf-naca4424-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -0.8521 0.08812 0.08337 -0.1000 0.9927 0.0661
-19.500 -0.8534 0.08408 0.07926 -0.1030 0.9919 0.0670
-19.250 -0.8554 0.08029 0.07540 -0.1052 0.9907 0.0680
-19.000 -0.8565 0.07665 0.07167 -0.1073 0.9892 0.0689
-18.750 -0.8626 0.07232 0.06730 -0.1100 0.9876 0.0698
-18.500 -0.8656 0.06838 0.06331 -0.1125 0.9860 0.0706
-18.250 -0.8676 0.06446 0.05932 -0.1152 0.9844 0.0716
-18.000 -0.8671 0.06079 0.05559 -0.1180 0.9829 0.0726
-17.750 -0.8645 0.05733 0.05205 -0.1207 0.9815 0.0737
-17.500 -0.8577 0.05430 0.04893 -0.1234 0.9803 0.0747
-17.250 -0.8540 0.05092 0.04549 -0.1263 0.9793 0.0757
-17.000 -0.8601 0.04769 0.04221 -0.1269 0.9750 0.0765
-16.750 -0.8593 0.04471 0.03917 -0.1285 0.9716 0.0779
-16.500 -0.8524 0.04212 0.03651 -0.1303 0.9691 0.0792
-16.250 -0.8415 0.03981 0.03414 -0.1323 0.9672 0.0805
-16.000 -0.8289 0.03760 0.03186 -0.1344 0.9657 0.0818
-15.750 -0.8332 0.03537 0.02959 -0.1335 0.9586 0.0827
-15.500 -0.8240 0.03332 0.02749 -0.1346 0.9550 0.0841
-15.250 -0.8097 0.03153 0.02566 -0.1361 0.9526 0.0855
-15.000 -0.7968 0.03000 0.02407 -0.1367 0.9491 0.0870
-14.750 -0.7894 0.02866 0.02267 -0.1359 0.9425 0.0882
-14.500 -0.7761 0.02709 0.02107 -0.1366 0.9387 0.0896
-14.250 -0.7574 0.02567 0.01962 -0.1379 0.9361 0.0917
-14.000 -0.7439 0.02454 0.01844 -0.1378 0.9304 0.0931
-13.750 -0.7234 0.02355 0.01740 -0.1385 0.9257 0.0951
-13.500 -0.6980 0.02244 0.01625 -0.1402 0.9221 0.0970
-13.250 -0.6680 0.02140 0.01518 -0.1427 0.9188 0.0992
-13.000 -0.6449 0.02060 0.01434 -0.1435 0.9119 0.1013
-12.750 -0.6157 0.01990 0.01358 -0.1451 0.9059 0.1034
-12.500 -0.5838 0.01909 0.01275 -0.1476 0.9008 0.1060
-12.250 -0.5604 0.01848 0.01209 -0.1481 0.8937 0.1085
-12.000 -0.5349 0.01797 0.01153 -0.1487 0.8858 0.1112
-11.750 -0.5025 0.01740 0.01092 -0.1508 0.8792 0.1140
-11.500 -0.4855 0.01694 0.01044 -0.1497 0.8708 0.1166
-11.250 -0.4605 0.01654 0.00999 -0.1500 0.8628 0.1194
-11.000 -0.4294 0.01614 0.00954 -0.1514 0.8558 0.1224
-10.750 -0.4154 0.01577 0.00915 -0.1495 0.8467 0.1253
-10.500 -0.3882 0.01545 0.00877 -0.1500 0.8378 0.1286
-10.250 -0.3689 0.01518 0.00846 -0.1489 0.8292 0.1313
-10.000 -0.3527 0.01487 0.00812 -0.1471 0.8189 0.1347
-9.750 -0.3342 0.01462 0.00782 -0.1457 0.8098 0.1379
-9.500 -0.3188 0.01442 0.00757 -0.1436 0.7995 0.1407
-9.250 -0.3020 0.01418 0.00729 -0.1417 0.7906 0.1439
-9.000 -0.2898 0.01398 0.00707 -0.1389 0.7807 0.1473
-8.750 -0.2734 0.01382 0.00684 -0.1368 0.7710 0.1506
-8.500 -0.2615 0.01367 0.00665 -0.1338 0.7608 0.1537
-8.250 -0.2494 0.01350 0.00645 -0.1308 0.7508 0.1572
-8.000 -0.2378 0.01336 0.00628 -0.1276 0.7414 0.1603
-7.750 -0.2258 0.01327 0.00612 -0.1244 0.7312 0.1641
-7.500 -0.2159 0.01314 0.00597 -0.1209 0.7222 0.1672
-7.250 -0.2092 0.01303 0.00583 -0.1166 0.7118 0.1710
-7.000 -0.2011 0.01296 0.00571 -0.1126 0.7030 0.1744
-6.750 -0.1948 0.01290 0.00561 -0.1081 0.6939 0.1775
-6.500 -0.1922 0.01283 0.00550 -0.1029 0.6850 0.1809
-6.250 -0.1880 0.01274 0.00540 -0.0980 0.6762 0.1845
-6.000 -0.1806 0.01269 0.00531 -0.0938 0.6666 0.1883
-5.750 -0.1693 0.01264 0.00520 -0.0903 0.6584 0.1919
-5.500 -0.1590 0.01253 0.00510 -0.0866 0.6498 0.1962
-5.250 -0.1487 0.01249 0.00501 -0.0829 0.6410 0.2004
-5.000 -0.1350 0.01243 0.00493 -0.0799 0.6331 0.2049
-4.750 -0.1240 0.01238 0.00486 -0.0764 0.6240 0.2090
-4.500 -0.1127 0.01234 0.00479 -0.0729 0.6163 0.2134
-4.250 -0.0979 0.01228 0.00473 -0.0701 0.6088 0.2186
-4.000 -0.0842 0.01227 0.00468 -0.0671 0.6007 0.2230
-3.750 -0.0708 0.01223 0.00463 -0.0641 0.5933 0.2284
-3.500 -0.0551 0.01219 0.00459 -0.0615 0.5858 0.2343
-3.250 -0.0404 0.01220 0.00456 -0.0587 0.5785 0.2390
-3.000 -0.0261 0.01217 0.00453 -0.0559 0.5722 0.2449
-2.750 -0.0092 0.01214 0.00451 -0.0535 0.5658 0.2514
-2.500 0.0070 0.01216 0.00450 -0.0511 0.5589 0.2571
-2.250 0.0214 0.01216 0.00449 -0.0483 0.5525 0.2638
-2.000 0.0400 0.01213 0.00448 -0.0463 0.5470 0.2712
-1.750 0.0575 0.01215 0.00449 -0.0441 0.5410 0.2768
-1.500 0.0723 0.01216 0.00450 -0.0414 0.5347 0.2841
-1.250 0.0893 0.01219 0.00452 -0.0391 0.5293 0.2912
-0.750 0.1259 0.01219 0.00456 -0.0351 0.5186 0.3060
-0.500 0.1430 0.01224 0.00460 -0.0329 0.5135 0.3140
-0.250 0.1600 0.01230 0.00464 -0.0307 0.5081 0.3209
0.000 0.1787 0.01229 0.00468 -0.0289 0.5035 0.3307
0.250 0.1974 0.01234 0.00474 -0.0270 0.4984 0.3385
0.500 0.2143 0.01239 0.00480 -0.0248 0.4929 0.3474
0.750 0.2313 0.01246 0.00487 -0.0227 0.4881 0.3578
1.000 0.2512 0.01249 0.00494 -0.0211 0.4840 0.3673
1.250 0.2697 0.01253 0.00502 -0.0193 0.4792 0.3791
1.500 0.2880 0.01259 0.00511 -0.0174 0.4746 0.3913
1.750 0.3045 0.01268 0.00521 -0.0153 0.4692 0.4048
2.000 0.3237 0.01274 0.00531 -0.0136 0.4650 0.4184
2.250 0.3429 0.01279 0.00543 -0.0120 0.4604 0.4352
2.500 0.3609 0.01285 0.00556 -0.0102 0.4555 0.4549
2.750 0.3782 0.01295 0.00570 -0.0083 0.4505 0.4750
3.000 0.3967 0.01302 0.00586 -0.0067 0.4464 0.5013
3.250 0.4167 0.01307 0.00602 -0.0053 0.4421 0.5283
3.500 0.4357 0.01316 0.00620 -0.0037 0.4371 0.5533
3.750 0.4538 0.01330 0.00640 -0.0021 0.4317 0.5789
4.000 0.4729 0.01344 0.00661 -0.0007 0.4267 0.6041
4.250 0.4952 0.01352 0.00680 0.0001 0.4224 0.6307
4.500 0.5167 0.01365 0.00703 0.0010 0.4176 0.6578
4.750 0.5374 0.01383 0.00729 0.0020 0.4122 0.6853
5.000 0.5606 0.01399 0.00756 0.0024 0.4076 0.7193
5.250 0.5899 0.01408 0.00782 0.0017 0.4025 0.7612
5.500 0.6353 0.01421 0.00817 -0.0025 0.3960 0.8197
5.750 0.7042 0.01451 0.00861 -0.0117 0.3887 0.8765
6.000 0.7984 0.01497 0.00918 -0.0258 0.3814 0.9132
6.250 0.8636 0.01566 0.00984 -0.0342 0.3731 0.9351
6.500 0.8960 0.01612 0.01029 -0.0357 0.3677 0.9558
7.000 0.9355 0.01714 0.01128 -0.0339 0.3566 0.9848
7.250 0.9631 0.01777 0.01188 -0.0347 0.3508 0.9908
7.500 0.9969 0.01834 0.01244 -0.0367 0.3445 0.9967
7.750 1.0360 0.01902 0.01307 -0.0400 0.3372 0.9999
8.000 1.0503 0.01948 0.01352 -0.0383 0.3328 1.0000
8.250 1.0626 0.01995 0.01400 -0.0362 0.3277 1.0000
8.500 1.0730 0.02053 0.01455 -0.0339 0.3221 1.0000
8.750 1.0826 0.02118 0.01518 -0.0315 0.3165 1.0000
9.000 1.0955 0.02173 0.01573 -0.0297 0.3114 1.0000
9.250 1.1057 0.02242 0.01640 -0.0276 0.3053 1.0000
9.500 1.1143 0.02322 0.01717 -0.0254 0.3001 1.0000
9.750 1.1266 0.02388 0.01784 -0.0236 0.2941 1.0000
10.000 1.1356 0.02473 0.01868 -0.0216 0.2881 1.0000
10.250 1.1444 0.02564 0.01957 -0.0197 0.2829 1.0000
10.500 1.1560 0.02642 0.02035 -0.0181 0.2769 1.0000
10.750 1.1636 0.02746 0.02139 -0.0162 0.2714 1.0000
11.000 1.1728 0.02845 0.02236 -0.0145 0.2659 1.0000
11.250 1.1823 0.02946 0.02338 -0.0129 0.2600 1.0000
11.500 1.1887 0.03069 0.02459 -0.0112 0.2543 1.0000
11.750 1.1975 0.03180 0.02571 -0.0097 0.2488 1.0000
12.000 1.2049 0.03304 0.02695 -0.0082 0.2429 1.0000
12.250 1.2090 0.03454 0.02844 -0.0066 0.2375 1.0000
12.500 1.2183 0.03574 0.02965 -0.0054 0.2321 1.0000
12.750 1.2247 0.03715 0.03107 -0.0041 0.2269 1.0000
13.000 1.2284 0.03881 0.03272 -0.0027 0.2218 1.0000
13.250 1.2356 0.04024 0.03417 -0.0016 0.2163 1.0000
13.500 1.2389 0.04200 0.03594 -0.0003 0.2114 1.0000
13.750 1.2439 0.04367 0.03761 0.0007 0.2073 1.0000
14.000 1.2491 0.04535 0.03932 0.0017 0.2019 1.0000
14.250 1.2513 0.04733 0.04130 0.0027 0.1971 1.0000
14.500 1.2552 0.04919 0.04319 0.0036 0.1934 1.0000
14.750 1.2603 0.05097 0.04499 0.0044 0.1887 1.0000
15.000 1.2612 0.05316 0.04719 0.0052 0.1843 1.0000
15.250 1.2635 0.05524 0.04929 0.0059 0.1805 1.0000
15.500 1.2672 0.05726 0.05134 0.0065 0.1762 1.0000
15.750 1.2672 0.05962 0.05371 0.0071 0.1718 1.0000
16.000 1.2679 0.06196 0.05607 0.0077 0.1683 1.0000
16.250 1.2716 0.06402 0.05817 0.0081 0.1642 1.0000
16.500 1.2695 0.06672 0.06087 0.0085 0.1597 1.0000
16.750 1.2701 0.06914 0.06332 0.0089 0.1564 1.0000
17.000 1.2720 0.07148 0.06570 0.0091 0.1528 1.0000
17.250 1.2716 0.07406 0.06829 0.0093 0.1488 1.0000
17.500 1.2685 0.07696 0.07122 0.0095 0.1454 1.0000
17.750 1.2712 0.07926 0.07356 0.0096 0.1418 1.0000
18.000 1.2692 0.08210 0.07642 0.0096 0.1383 1.0000
18.250 1.2664 0.08505 0.07939 0.0096 0.1351 1.0000
18.500 1.2687 0.08745 0.08183 0.0095 0.1323 1.0000
18.750 1.2679 0.09021 0.08463 0.0094 0.1291 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 4424 (naca4424-il)