AH 83-150 Q (ah83150q-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 83-150 Q (ah83150q-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.76 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah83150q-il-1000000-n5.txt Download as CSV file: xf-ah83150q-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 83-150 Q
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1838 0.10364 0.10080 -0.0438 0.6560 0.0057
-11.000 -0.2537 0.10371 0.10066 -0.0514 0.6630 0.0048
-10.750 -0.2521 0.09938 0.09633 -0.0535 0.6616 0.0048
-10.500 -0.2458 0.09673 0.09368 -0.0549 0.6599 0.0046
-10.250 -0.2466 0.09203 0.08899 -0.0571 0.6586 0.0046
-10.000 -0.2465 0.08779 0.08475 -0.0592 0.6570 0.0046
-9.750 -0.2490 0.08314 0.08012 -0.0618 0.6557 0.0054
-9.250 -0.2549 0.07398 0.07099 -0.0670 0.6531 0.0045
-9.000 -0.2211 0.05558 0.05281 -0.0649 0.6476 0.0053
-8.500 -0.3289 0.05376 0.05071 -0.0770 0.6490 0.0052
-8.250 -0.3363 0.04841 0.04522 -0.0764 0.6475 0.0050
-8.000 -0.3477 0.04331 0.03993 -0.0752 0.6458 0.0051
-7.750 -0.3484 0.03816 0.03454 -0.0736 0.6442 0.0051
-7.500 -0.3441 0.03345 0.02957 -0.0719 0.6427 0.0050
-7.250 -0.3391 0.02878 0.02453 -0.0699 0.6412 0.0050
-7.000 -0.3233 0.02641 0.02190 -0.0689 0.6396 0.0050
-6.750 -0.3123 0.02263 0.01766 -0.0672 0.6382 0.0051
-6.500 -0.2929 0.02060 0.01538 -0.0665 0.6369 0.0052
-6.250 -0.2702 0.01915 0.01373 -0.0660 0.6354 0.0053
-6.000 -0.2467 0.01745 0.01175 -0.0654 0.6337 0.0051
-5.750 -0.2214 0.01644 0.01058 -0.0651 0.6321 0.0051
-5.500 -0.1954 0.01561 0.00961 -0.0649 0.6305 0.0051
-5.250 -0.1695 0.01470 0.00857 -0.0647 0.6288 0.0050
-5.000 -0.1430 0.01402 0.00778 -0.0646 0.6270 0.0050
-4.750 -0.1168 0.01324 0.00689 -0.0644 0.6252 0.0050
-4.500 -0.0904 0.01261 0.00617 -0.0642 0.6236 0.0050
-4.250 -0.0640 0.01198 0.00549 -0.0641 0.6222 0.0051
-4.000 -0.0375 0.01141 0.00487 -0.0640 0.6207 0.0051
-3.750 -0.0108 0.01092 0.00434 -0.0639 0.6190 0.0052
-3.500 0.0164 0.01053 0.00392 -0.0640 0.6172 0.0053
-3.250 0.0439 0.01021 0.00357 -0.0640 0.6155 0.0054
-3.000 0.0717 0.00995 0.00328 -0.0642 0.6138 0.0056
-2.750 0.0997 0.00971 0.00303 -0.0643 0.6119 0.0059
-2.500 0.1277 0.00952 0.00280 -0.0645 0.6100 0.0062
-2.250 0.1560 0.00935 0.00261 -0.0646 0.6081 0.0068
-2.000 0.1846 0.00919 0.00245 -0.0649 0.6066 0.0071
-1.750 0.2131 0.00902 0.00227 -0.0652 0.6047 0.0078
-1.500 0.2418 0.00889 0.00215 -0.0654 0.6025 0.0086
-1.250 0.2706 0.00879 0.00203 -0.0657 0.6000 0.0098
-1.000 0.2992 0.00868 0.00192 -0.0660 0.5975 0.0133
-0.750 0.3267 0.00832 0.00180 -0.0663 0.5951 0.0922
-0.500 0.3529 0.00762 0.00169 -0.0666 0.5928 0.2928
-0.250 0.3746 0.00609 0.00166 -0.0665 0.5906 0.7542
0.000 0.4030 0.00625 0.00187 -0.0665 0.5880 0.7930
0.250 0.4315 0.00643 0.00205 -0.0665 0.5852 0.8073
0.500 0.4607 0.00655 0.00212 -0.0668 0.5823 0.8138
0.750 0.4896 0.00661 0.00214 -0.0671 0.5795 0.8167
1.000 0.5187 0.00666 0.00218 -0.0674 0.5768 0.8186
1.250 0.5480 0.00668 0.00219 -0.0678 0.5734 0.8196
1.500 0.5773 0.00671 0.00220 -0.0683 0.5696 0.8203
1.750 0.6064 0.00676 0.00221 -0.0687 0.5658 0.8212
2.000 0.6355 0.00680 0.00223 -0.0691 0.5622 0.8221
2.250 0.6648 0.00683 0.00225 -0.0696 0.5582 0.8229
2.500 0.6939 0.00687 0.00228 -0.0700 0.5538 0.8236
2.750 0.7227 0.00693 0.00231 -0.0704 0.5493 0.8243
3.000 0.7518 0.00697 0.00235 -0.0709 0.5448 0.8252
3.250 0.7807 0.00703 0.00240 -0.0713 0.5392 0.8261
3.500 0.8092 0.00711 0.00245 -0.0716 0.5338 0.8269
3.750 0.8381 0.00717 0.00251 -0.0721 0.5276 0.8276
4.250 0.8946 0.00735 0.00265 -0.0728 0.5115 0.8289
4.500 0.9219 0.00751 0.00275 -0.0730 0.4966 0.8294
4.750 0.9482 0.00773 0.00289 -0.0730 0.4775 0.8301
5.000 0.9740 0.00798 0.00306 -0.0730 0.4573 0.8308
5.250 0.9999 0.00820 0.00323 -0.0730 0.4412 0.8316
5.500 1.0254 0.00845 0.00342 -0.0730 0.4242 0.8322
5.750 1.0502 0.00874 0.00365 -0.0728 0.4065 0.8329
6.000 1.0751 0.00901 0.00387 -0.0727 0.3918 0.8335
6.250 1.0995 0.00929 0.00411 -0.0725 0.3768 0.8341
6.500 1.1227 0.00964 0.00440 -0.0721 0.3588 0.8348
6.750 1.1452 0.01001 0.00470 -0.0716 0.3412 0.8355
7.000 1.1677 0.01035 0.00499 -0.0711 0.3261 0.8364
7.250 1.1890 0.01074 0.00533 -0.0704 0.3097 0.8373
7.500 1.2087 0.01117 0.00570 -0.0695 0.2908 0.8382
7.750 1.2248 0.01174 0.00615 -0.0681 0.2675 0.8391
8.000 1.2357 0.01246 0.00673 -0.0658 0.2382 0.8401
8.250 1.2390 0.01321 0.00735 -0.0622 0.2111 0.8413
8.500 1.2384 0.01414 0.00816 -0.0581 0.1876 0.8426
8.750 1.2452 0.01494 0.00892 -0.0556 0.1744 0.8437
9.000 1.2522 0.01587 0.00980 -0.0534 0.1614 0.8446
9.250 1.2597 0.01688 0.01078 -0.0515 0.1494 0.8457
9.500 1.2687 0.01786 0.01174 -0.0498 0.1394 0.8469
9.750 1.2786 0.01886 0.01274 -0.0484 0.1307 0.8479
10.000 1.2875 0.01996 0.01382 -0.0470 0.1224 0.8489
10.250 1.2963 0.02110 0.01495 -0.0456 0.1135 0.8498
10.500 1.3070 0.02215 0.01601 -0.0444 0.1073 0.8507
10.750 1.3132 0.02352 0.01734 -0.0430 0.0968 0.8517
11.000 1.3229 0.02468 0.01851 -0.0419 0.0896 0.8526
11.250 1.3291 0.02611 0.01990 -0.0406 0.0795 0.8536
11.500 1.3385 0.02734 0.02114 -0.0396 0.0748 0.8545
11.750 1.3463 0.02871 0.02250 -0.0385 0.0671 0.8554
12.000 1.3489 0.03049 0.02422 -0.0372 0.0558 0.8563
12.250 1.3551 0.03203 0.02576 -0.0361 0.0494 0.8573
12.500 1.3622 0.03356 0.02729 -0.0352 0.0446 0.8583
12.750 1.3697 0.03512 0.02886 -0.0345 0.0402 0.8591
13.000 1.3766 0.03675 0.03050 -0.0337 0.0363 0.8598
13.250 1.3854 0.03829 0.03208 -0.0332 0.0339 0.8606
13.500 1.3941 0.03984 0.03366 -0.0327 0.0315 0.8615
13.750 1.4017 0.04154 0.03539 -0.0321 0.0295 0.8624
14.000 1.4097 0.04323 0.03713 -0.0317 0.0274 0.8632
14.250 1.4175 0.04497 0.03891 -0.0313 0.0255 0.8641
14.500 1.4236 0.04693 0.04089 -0.0310 0.0233 0.8650
14.750 1.4316 0.04874 0.04276 -0.0307 0.0222 0.8659
15.000 1.4393 0.05061 0.04468 -0.0306 0.0208 0.8667
15.250 1.4446 0.05275 0.04685 -0.0304 0.0186 0.8676
15.500 1.4503 0.05494 0.04908 -0.0303 0.0169 0.8685
15.750 1.4565 0.05709 0.05128 -0.0303 0.0153 0.8694
16.000 1.4595 0.05963 0.05387 -0.0304 0.0128 0.8703
16.250 1.4592 0.06261 0.05685 -0.0305 0.0089 0.8712
16.500 1.4579 0.06580 0.06007 -0.0307 0.0059 0.8720
16.750 1.4560 0.06917 0.06349 -0.0310 0.0042 0.8727
17.000 1.4555 0.07242 0.06681 -0.0315 0.0034 0.8734
17.250 1.4567 0.07551 0.06997 -0.0320 0.0029 0.8741
17.750 1.4596 0.08181 0.07645 -0.0334 0.0026 0.8759
18.000 1.4597 0.08522 0.07995 -0.0343 0.0024 0.8770
18.250 1.4581 0.08892 0.08374 -0.0352 0.0023 0.8780
18.500 1.4553 0.09287 0.08780 -0.0364 0.0021 0.8791
18.750 1.4547 0.09658 0.09160 -0.0376 0.0020 0.8802
19.000 1.4540 0.10031 0.09543 -0.0389 0.0020 0.8814
19.250 1.4517 0.10436 0.09958 -0.0404 0.0018 0.8825
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Polar data table (+)
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