NACA 2410 (naca2410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2410 (naca2410-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.47 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2410-il-1000000.txt Download as CSV file: xf-naca2410-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2410
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -1.0113 0.07601 0.07376 -0.0290 1.0000 0.0088
-14.750 -1.0707 0.06077 0.05831 -0.0388 1.0000 0.0084
-14.500 -1.0990 0.04855 0.04588 -0.0492 1.0000 0.0083
-14.250 -1.1169 0.03930 0.03639 -0.0596 1.0000 0.0082
-14.000 -1.1355 0.03436 0.03122 -0.0623 1.0000 0.0083
-13.750 -1.1483 0.03120 0.02784 -0.0608 1.0000 0.0084
-13.500 -1.1470 0.02874 0.02521 -0.0597 1.0000 0.0086
-13.250 -1.1370 0.02706 0.02341 -0.0587 1.0000 0.0089
-13.000 -1.1225 0.02580 0.02205 -0.0579 1.0000 0.0091
-12.750 -1.1061 0.02473 0.02088 -0.0570 1.0000 0.0094
-12.500 -1.0891 0.02369 0.01974 -0.0562 1.0000 0.0096
-12.250 -1.0717 0.02270 0.01864 -0.0552 1.0000 0.0099
-12.000 -1.0542 0.02174 0.01756 -0.0541 1.0000 0.0102
-11.750 -1.0364 0.02087 0.01657 -0.0529 1.0000 0.0105
-11.500 -1.0177 0.02013 0.01573 -0.0517 1.0000 0.0107
-11.250 -1.0026 0.01894 0.01438 -0.0501 1.0000 0.0110
-11.000 -0.9873 0.01780 0.01313 -0.0484 1.0000 0.0117
-10.750 -0.9684 0.01713 0.01241 -0.0471 1.0000 0.0122
-10.500 -0.9489 0.01659 0.01181 -0.0458 1.0000 0.0126
-10.250 -0.9292 0.01607 0.01122 -0.0444 1.0000 0.0132
-10.000 -0.9092 0.01560 0.01068 -0.0431 1.0000 0.0137
-9.750 -0.8885 0.01525 0.01026 -0.0419 1.0000 0.0141
-9.500 -0.8707 0.01438 0.00932 -0.0403 1.0000 0.0154
-9.250 -0.8497 0.01404 0.00898 -0.0392 1.0000 0.0164
-9.000 -0.8227 0.01373 0.00863 -0.0393 0.9995 0.0174
-8.750 -0.7897 0.01344 0.00829 -0.0405 0.9983 0.0183
-8.500 -0.7577 0.01282 0.00765 -0.0417 0.9970 0.0202
-8.250 -0.7238 0.01265 0.00748 -0.0432 0.9958 0.0218
-8.000 -0.6892 0.01253 0.00735 -0.0447 0.9948 0.0232
-7.750 -0.6567 0.01203 0.00679 -0.0459 0.9934 0.0250
-7.500 -0.6240 0.01175 0.00652 -0.0471 0.9913 0.0267
-7.250 -0.5896 0.01153 0.00629 -0.0486 0.9893 0.0283
-7.000 -0.5542 0.01138 0.00611 -0.0503 0.9877 0.0297
-6.750 -0.5195 0.01093 0.00561 -0.0519 0.9863 0.0312
-6.500 -0.4850 0.01042 0.00509 -0.0535 0.9852 0.0334
-6.250 -0.4522 0.01016 0.00483 -0.0547 0.9829 0.0351
-6.000 -0.4204 0.00991 0.00455 -0.0555 0.9797 0.0365
-5.750 -0.3876 0.00968 0.00430 -0.0566 0.9770 0.0376
-5.500 -0.3551 0.00940 0.00398 -0.0576 0.9744 0.0386
-5.250 -0.3277 0.00896 0.00350 -0.0575 0.9687 0.0410
-5.000 -0.2986 0.00868 0.00321 -0.0577 0.9637 0.0430
-4.750 -0.2708 0.00846 0.00297 -0.0576 0.9576 0.0450
-4.500 -0.2435 0.00826 0.00275 -0.0573 0.9506 0.0467
-4.250 -0.2163 0.00806 0.00251 -0.0570 0.9433 0.0492
-4.000 -0.1895 0.00781 0.00228 -0.0566 0.9351 0.0557
-3.750 -0.1627 0.00756 0.00208 -0.0563 0.9264 0.0701
-3.500 -0.1361 0.00730 0.00190 -0.0560 0.9174 0.0952
-3.250 -0.1091 0.00710 0.00176 -0.0557 0.9070 0.1166
-3.000 -0.0820 0.00692 0.00164 -0.0554 0.8967 0.1398
-2.750 -0.0550 0.00675 0.00152 -0.0552 0.8856 0.1649
-2.500 -0.0278 0.00659 0.00142 -0.0550 0.8732 0.1923
-2.250 -0.0006 0.00643 0.00133 -0.0548 0.8603 0.2226
-2.000 0.0267 0.00629 0.00125 -0.0546 0.8466 0.2560
-1.750 0.0539 0.00616 0.00118 -0.0544 0.8322 0.2923
-1.500 0.0810 0.00600 0.00112 -0.0542 0.8169 0.3389
-1.250 0.1077 0.00578 0.00107 -0.0540 0.8008 0.4051
-1.000 0.1344 0.00558 0.00103 -0.0538 0.7841 0.4750
-0.750 0.1610 0.00541 0.00101 -0.0535 0.7669 0.5452
-0.500 0.1874 0.00523 0.00100 -0.0532 0.7492 0.6212
-0.250 0.2133 0.00504 0.00102 -0.0527 0.7308 0.7045
0.000 0.2392 0.00493 0.00103 -0.0521 0.7117 0.7654
0.250 0.2641 0.00482 0.00107 -0.0512 0.6922 0.8319
0.500 0.2876 0.00476 0.00113 -0.0499 0.6727 0.8963
0.750 0.3127 0.00479 0.00118 -0.0490 0.6524 0.9398
1.000 0.3433 0.00489 0.00122 -0.0494 0.6316 0.9661
1.250 0.3777 0.00501 0.00126 -0.0507 0.6108 0.9815
1.500 0.4143 0.00514 0.00130 -0.0526 0.5891 0.9908
2.000 0.4881 0.00546 0.00141 -0.0566 0.5404 1.0000
2.250 0.5127 0.00565 0.00146 -0.0560 0.5093 1.0000
2.500 0.5377 0.00580 0.00152 -0.0554 0.4854 1.0000
2.750 0.5629 0.00596 0.00159 -0.0548 0.4640 1.0000
3.000 0.5883 0.00611 0.00166 -0.0543 0.4456 1.0000
3.250 0.6135 0.00628 0.00175 -0.0537 0.4217 1.0000
3.500 0.6386 0.00649 0.00186 -0.0532 0.3949 1.0000
3.750 0.6637 0.00674 0.00198 -0.0527 0.3654 1.0000
4.000 0.6888 0.00700 0.00211 -0.0522 0.3350 1.0000
4.250 0.7138 0.00730 0.00228 -0.0516 0.3009 1.0000
4.500 0.7383 0.00767 0.00248 -0.0511 0.2622 1.0000
4.750 0.7625 0.00810 0.00271 -0.0505 0.2206 1.0000
5.000 0.7865 0.00856 0.00297 -0.0499 0.1792 1.0000
5.250 0.8102 0.00907 0.00328 -0.0493 0.1372 1.0000
5.500 0.8339 0.00958 0.00360 -0.0487 0.1010 1.0000
5.750 0.8575 0.01011 0.00396 -0.0480 0.0694 1.0000
6.000 0.8816 0.01059 0.00431 -0.0475 0.0500 1.0000
6.250 0.9065 0.01098 0.00466 -0.0469 0.0432 1.0000
6.500 0.9321 0.01126 0.00496 -0.0466 0.0413 1.0000
6.750 0.9573 0.01159 0.00530 -0.0461 0.0391 1.0000
7.000 0.9820 0.01197 0.00569 -0.0456 0.0369 1.0000
7.250 1.0056 0.01249 0.00625 -0.0449 0.0347 1.0000
7.500 1.0310 0.01275 0.00654 -0.0446 0.0341 1.0000
7.750 1.0560 0.01305 0.00688 -0.0441 0.0332 1.0000
8.000 1.0807 0.01339 0.00724 -0.0437 0.0320 1.0000
8.250 1.1050 0.01375 0.00764 -0.0432 0.0309 1.0000
8.500 1.1285 0.01419 0.00808 -0.0426 0.0294 1.0000
8.750 1.1489 0.01494 0.00889 -0.0415 0.0275 1.0000
9.000 1.1721 0.01537 0.00937 -0.0408 0.0268 1.0000
9.250 1.1967 0.01564 0.00967 -0.0404 0.0260 1.0000
9.500 1.2207 0.01594 0.01000 -0.0399 0.0249 1.0000
9.750 1.2445 0.01626 0.01033 -0.0394 0.0236 1.0000
10.000 1.2667 0.01673 0.01079 -0.0387 0.0223 1.0000
10.250 1.2852 0.01751 0.01165 -0.0374 0.0208 1.0000
10.500 1.3095 0.01773 0.01189 -0.0370 0.0200 1.0000
10.750 1.3328 0.01803 0.01222 -0.0364 0.0188 1.0000
11.000 1.3554 0.01836 0.01254 -0.0358 0.0175 1.0000
11.250 1.3730 0.01911 0.01331 -0.0344 0.0159 1.0000
11.500 1.3946 0.01948 0.01373 -0.0336 0.0151 1.0000
11.750 1.4146 0.01995 0.01423 -0.0326 0.0141 1.0000
12.000 1.4328 0.02055 0.01483 -0.0314 0.0132 1.0000
12.250 1.4429 0.02158 0.01592 -0.0290 0.0121 1.0000
12.500 1.4575 0.02221 0.01662 -0.0272 0.0117 1.0000
12.750 1.4704 0.02295 0.01744 -0.0252 0.0112 1.0000
13.000 1.4825 0.02377 0.01832 -0.0233 0.0107 1.0000
13.250 1.4932 0.02470 0.01932 -0.0214 0.0103 1.0000
13.500 1.5013 0.02585 0.02053 -0.0194 0.0098 1.0000
13.750 1.5035 0.02749 0.02227 -0.0169 0.0093 1.0000
14.000 1.5049 0.02929 0.02419 -0.0148 0.0090 1.0000
14.250 1.5134 0.03061 0.02561 -0.0135 0.0088 1.0000
14.500 1.5198 0.03217 0.02727 -0.0123 0.0086 1.0000
14.750 1.5250 0.03394 0.02913 -0.0112 0.0083 1.0000
15.000 1.5283 0.03597 0.03126 -0.0104 0.0081 1.0000
15.250 1.5302 0.03827 0.03367 -0.0098 0.0079 1.0000
15.500 1.5309 0.04083 0.03634 -0.0094 0.0078 1.0000
15.750 1.5297 0.04373 0.03935 -0.0094 0.0076 1.0000
16.000 1.5263 0.04707 0.04280 -0.0097 0.0075 1.0000
16.250 1.5205 0.05084 0.04669 -0.0104 0.0073 1.0000
16.500 1.5117 0.05520 0.05117 -0.0116 0.0072 1.0000
16.750 1.4997 0.06019 0.05630 -0.0132 0.0071 1.0000
17.000 1.4850 0.06578 0.06202 -0.0152 0.0071 1.0000
17.250 1.4668 0.07214 0.06853 -0.0177 0.0070 1.0000
17.500 1.4479 0.07880 0.07533 -0.0205 0.0069 1.0000
17.750 1.4265 0.08610 0.08277 -0.0238 0.0069 1.0000
18.000 1.4057 0.09351 0.09032 -0.0271 0.0069 1.0000
18.250 1.3828 0.10145 0.09840 -0.0309 0.0069 1.0000
18.500 1.3608 0.10948 0.10656 -0.0347 0.0069 1.0000
18.750 1.3376 0.11792 0.11513 -0.0389 0.0069 1.0000
19.000 1.3150 0.12641 0.12374 -0.0432 0.0069 1.0000
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