NACA 0024 (naca0024-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0024 (naca0024-il) Reynolds number: 200,000 Max Cl/Cd: 36.97 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0024-il-200000-n5.txt Download as CSV file: xf-naca0024-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0024
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0666 0.10389 0.09722 -0.0414 1.0000 0.1002
-19.500 -1.0711 0.10001 0.09322 -0.0429 1.0000 0.1021
-19.250 -1.0696 0.09711 0.09035 -0.0440 1.0000 0.1038
-19.000 -1.0710 0.09377 0.08697 -0.0452 1.0000 0.1057
-18.750 -1.0740 0.09018 0.08330 -0.0464 1.0000 0.1078
-18.500 -1.0769 0.08662 0.07963 -0.0476 1.0000 0.1100
-18.250 -1.0768 0.08361 0.07660 -0.0485 1.0000 0.1119
-18.000 -1.0774 0.08052 0.07350 -0.0494 1.0000 0.1140
-17.750 -1.0783 0.07736 0.07028 -0.0503 1.0000 0.1162
-17.500 -1.0789 0.07426 0.06708 -0.0511 1.0000 0.1186
-17.250 -1.0780 0.07141 0.06418 -0.0518 1.0000 0.1208
-17.000 -1.0780 0.06855 0.06131 -0.0524 1.0000 0.1230
-16.750 -1.0774 0.06576 0.05848 -0.0529 1.0000 0.1254
-16.500 -1.0757 0.06310 0.05574 -0.0534 1.0000 0.1280
-16.250 -1.0730 0.06060 0.05316 -0.0537 1.0000 0.1306
-16.000 -1.0718 0.05805 0.05063 -0.0540 1.0000 0.1329
-15.750 -1.0701 0.05557 0.04811 -0.0542 1.0000 0.1357
-15.500 -1.0662 0.05334 0.04582 -0.0543 1.0000 0.1386
-15.250 -1.0616 0.05123 0.04364 -0.0542 1.0000 0.1414
-15.000 -1.0594 0.04900 0.04141 -0.0541 1.0000 0.1441
-14.750 -1.0556 0.04695 0.03934 -0.0539 1.0000 0.1471
-14.500 -1.0501 0.04509 0.03742 -0.0536 1.0000 0.1504
-14.250 -1.0447 0.04332 0.03561 -0.0532 1.0000 0.1534
-14.000 -1.0411 0.04148 0.03378 -0.0525 1.0000 0.1565
-13.750 -1.0360 0.03982 0.03209 -0.0518 1.0000 0.1600
-13.500 -1.0285 0.03841 0.03061 -0.0511 1.0000 0.1636
-13.250 -1.0244 0.03689 0.02910 -0.0500 1.0000 0.1667
-13.000 -1.0202 0.03546 0.02767 -0.0487 1.0000 0.1702
-12.750 -1.0145 0.03425 0.02643 -0.0473 1.0000 0.1741
-12.500 -1.0088 0.03315 0.02529 -0.0456 1.0000 0.1778
-12.250 -1.0076 0.03198 0.02415 -0.0434 1.0000 0.1812
-12.000 -1.0054 0.03099 0.02315 -0.0410 1.0000 0.1849
-11.750 -1.0024 0.03016 0.02229 -0.0385 1.0000 0.1889
-11.500 -1.0027 0.02934 0.02147 -0.0353 1.0000 0.1923
-11.250 -1.0063 0.02856 0.02072 -0.0316 1.0000 0.1958
-11.000 -1.0068 0.02789 0.02004 -0.0282 0.9996 0.1997
-10.750 -0.9795 0.02702 0.01912 -0.0298 0.9953 0.2053
-10.500 -0.9548 0.02605 0.01818 -0.0312 0.9912 0.2109
-10.250 -0.9294 0.02524 0.01735 -0.0322 0.9854 0.2169
-10.000 -0.9024 0.02446 0.01657 -0.0335 0.9802 0.2226
-9.750 -0.8735 0.02367 0.01580 -0.0351 0.9761 0.2292
-9.500 -0.8486 0.02307 0.01515 -0.0356 0.9684 0.2353
-9.250 -0.8229 0.02232 0.01446 -0.0364 0.9620 0.2415
-9.000 -0.7988 0.02174 0.01386 -0.0366 0.9541 0.2482
-8.750 -0.7739 0.02117 0.01329 -0.0368 0.9457 0.2544
-8.500 -0.7510 0.02060 0.01274 -0.0367 0.9371 0.2611
-8.250 -0.7277 0.02015 0.01225 -0.0363 0.9271 0.2680
-8.000 -0.7065 0.01962 0.01176 -0.0356 0.9173 0.2743
-7.750 -0.6859 0.01919 0.01132 -0.0346 0.9062 0.2814
-7.500 -0.6644 0.01880 0.01089 -0.0337 0.8954 0.2880
-7.250 -0.6453 0.01837 0.01049 -0.0324 0.8837 0.2948
-7.000 -0.6253 0.01804 0.01013 -0.0310 0.8719 0.3021
-6.750 -0.6054 0.01768 0.00975 -0.0297 0.8601 0.3088
-6.500 -0.5877 0.01739 0.00946 -0.0278 0.8475 0.3162
-6.000 -0.5503 0.01688 0.00891 -0.0244 0.8227 0.3305
-5.750 -0.5292 0.01665 0.00863 -0.0231 0.8112 0.3384
-5.500 -0.5089 0.01645 0.00841 -0.0217 0.7978 0.3456
-5.250 -0.4879 0.01623 0.00817 -0.0204 0.7861 0.3535
-5.000 -0.4658 0.01607 0.00797 -0.0192 0.7730 0.3615
-4.750 -0.4444 0.01587 0.00776 -0.0180 0.7609 0.3691
-4.500 -0.4224 0.01572 0.00758 -0.0168 0.7480 0.3775
-4.250 -0.3995 0.01558 0.00740 -0.0158 0.7359 0.3854
-4.000 -0.3776 0.01543 0.00724 -0.0146 0.7231 0.3937
-3.750 -0.3541 0.01533 0.00709 -0.0137 0.7112 0.4024
-3.500 -0.3316 0.01519 0.00695 -0.0126 0.6987 0.4104
-3.250 -0.3086 0.01509 0.00683 -0.0116 0.6866 0.4196
-3.000 -0.2851 0.01500 0.00670 -0.0107 0.6746 0.4279
-2.750 -0.2621 0.01491 0.00661 -0.0097 0.6628 0.4369
-2.500 -0.2381 0.01486 0.00649 -0.0088 0.6509 0.4460
-2.250 -0.2149 0.01476 0.00643 -0.0078 0.6395 0.4547
-2.000 -0.1911 0.01472 0.00633 -0.0069 0.6279 0.4643
-1.750 -0.1674 0.01465 0.00628 -0.0061 0.6169 0.4731
-1.500 -0.1437 0.01461 0.00622 -0.0051 0.6056 0.4828
-1.250 -0.1196 0.01457 0.00617 -0.0043 0.5947 0.4921
-1.000 -0.0960 0.01454 0.00613 -0.0034 0.5836 0.5018
-0.750 -0.0717 0.01453 0.00609 -0.0026 0.5733 0.5118
-0.500 -0.0481 0.01449 0.00608 -0.0017 0.5623 0.5215
-0.250 -0.0239 0.01450 0.00606 -0.0009 0.5524 0.5319
0.000 0.0000 0.01448 0.00607 0.0000 0.5416 0.5416
0.250 0.0239 0.01450 0.00606 0.0009 0.5319 0.5524
0.500 0.0481 0.01449 0.00608 0.0017 0.5215 0.5623
0.750 0.0717 0.01453 0.00609 0.0026 0.5118 0.5733
1.000 0.0960 0.01454 0.00613 0.0034 0.5018 0.5837
1.250 0.1196 0.01457 0.00617 0.0043 0.4921 0.5947
1.500 0.1437 0.01461 0.00622 0.0051 0.4828 0.6056
1.750 0.1674 0.01465 0.00628 0.0061 0.4731 0.6169
2.000 0.1912 0.01472 0.00633 0.0069 0.4643 0.6279
2.250 0.2150 0.01476 0.00643 0.0078 0.4547 0.6395
2.500 0.2381 0.01486 0.00649 0.0088 0.4460 0.6510
2.750 0.2621 0.01491 0.00661 0.0096 0.4369 0.6627
3.000 0.2852 0.01500 0.00670 0.0106 0.4279 0.6746
3.250 0.3086 0.01509 0.00683 0.0116 0.4196 0.6867
3.500 0.3317 0.01519 0.00695 0.0126 0.4105 0.6987
3.750 0.3542 0.01533 0.00709 0.0137 0.4024 0.7112
4.000 0.3777 0.01543 0.00724 0.0146 0.3937 0.7231
4.250 0.3997 0.01558 0.00740 0.0158 0.3854 0.7359
4.500 0.4226 0.01572 0.00758 0.0168 0.3775 0.7480
4.750 0.4446 0.01587 0.00776 0.0179 0.3691 0.7609
5.000 0.4660 0.01607 0.00796 0.0192 0.3615 0.7730
5.250 0.4881 0.01623 0.00817 0.0203 0.3535 0.7861
5.500 0.5091 0.01645 0.00841 0.0216 0.3456 0.7978
5.750 0.5295 0.01665 0.00863 0.0230 0.3384 0.8113
6.000 0.5506 0.01688 0.00891 0.0244 0.3305 0.8227
6.500 0.5882 0.01739 0.00946 0.0278 0.3161 0.8475
6.750 0.6058 0.01768 0.00975 0.0296 0.3088 0.8601
7.000 0.6258 0.01804 0.01012 0.0310 0.3021 0.8719
7.250 0.6458 0.01837 0.01048 0.0323 0.2948 0.8837
7.500 0.6649 0.01880 0.01089 0.0336 0.2879 0.8954
7.750 0.6864 0.01918 0.01131 0.0346 0.2813 0.9062
8.000 0.7070 0.01962 0.01175 0.0355 0.2743 0.9173
8.250 0.7283 0.02014 0.01224 0.0362 0.2679 0.9271
8.500 0.7515 0.02059 0.01273 0.0366 0.2611 0.9372
8.750 0.7745 0.02116 0.01328 0.0367 0.2544 0.9457
9.000 0.7995 0.02173 0.01385 0.0365 0.2482 0.9542
9.250 0.8236 0.02231 0.01445 0.0363 0.2414 0.9621
9.500 0.8494 0.02305 0.01514 0.0354 0.2353 0.9685
9.750 0.8744 0.02365 0.01578 0.0350 0.2291 0.9762
10.000 0.9033 0.02444 0.01655 0.0333 0.2226 0.9803
10.250 0.9304 0.02522 0.01733 0.0320 0.2168 0.9856
10.500 0.9559 0.02603 0.01816 0.0310 0.2108 0.9912
10.750 0.9807 0.02700 0.01910 0.0296 0.2053 0.9954
11.000 1.0081 0.02786 0.02001 0.0280 0.1996 0.9997
11.250 1.0065 0.02852 0.02068 0.0316 0.1958 1.0000
11.500 1.0030 0.02930 0.02143 0.0353 0.1923 1.0000
11.750 1.0029 0.03011 0.02225 0.0384 0.1889 1.0000
12.000 1.0060 0.03094 0.02310 0.0410 0.1849 1.0000
12.250 1.0083 0.03193 0.02409 0.0434 0.1811 1.0000
12.500 1.0097 0.03311 0.02524 0.0455 0.1777 1.0000
12.750 1.0156 0.03420 0.02637 0.0472 0.1741 1.0000
13.000 1.0215 0.03541 0.02762 0.0485 0.1702 1.0000
13.250 1.0258 0.03684 0.02904 0.0498 0.1667 1.0000
13.500 1.0302 0.03836 0.03055 0.0509 0.1635 1.0000
13.750 1.0377 0.03977 0.03203 0.0516 0.1599 1.0000
14.000 1.0429 0.04142 0.03372 0.0523 0.1564 1.0000
14.250 1.0467 0.04326 0.03555 0.0529 0.1533 1.0000
14.500 1.0523 0.04503 0.03735 0.0533 0.1503 1.0000
14.750 1.0579 0.04688 0.03927 0.0536 0.1470 1.0000
15.000 1.0617 0.04893 0.04134 0.0538 0.1439 1.0000
15.250 1.0640 0.05116 0.04357 0.0539 0.1413 1.0000
15.500 1.0688 0.05326 0.04574 0.0539 0.1385 1.0000
15.750 1.0727 0.05550 0.04804 0.0538 0.1355 1.0000
16.000 1.0745 0.05798 0.05055 0.0536 0.1328 1.0000
16.250 1.0758 0.06052 0.05308 0.0533 0.1305 1.0000
16.500 1.0787 0.06301 0.05565 0.0530 0.1279 1.0000
16.750 1.0804 0.06568 0.05840 0.0525 0.1253 1.0000
17.000 1.0811 0.06846 0.06122 0.0520 0.1229 1.0000
17.250 1.0812 0.07133 0.06409 0.0514 0.1207 1.0000
17.500 1.0822 0.07417 0.06700 0.0507 0.1185 1.0000
17.750 1.0817 0.07727 0.07019 0.0499 0.1161 1.0000
18.000 1.0808 0.08044 0.07341 0.0490 0.1138 1.0000
18.250 1.0804 0.08351 0.07650 0.0481 0.1119 1.0000
18.500 1.0804 0.08655 0.07956 0.0472 0.1099 1.0000
18.750 1.0776 0.09011 0.08323 0.0460 0.1077 1.0000
19.000 1.0747 0.09369 0.08689 0.0447 0.1056 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0024 (naca0024-il)