NACA 66 (p51hroot-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66 (p51hroot-il) Reynolds number: 500,000 Max Cl/Cd: 67.21 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51hroot-il-500000.txt Download as CSV file: xf-p51hroot-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4197 0.08175 0.07913 -0.0679 0.8541 0.0332
-12.250 -0.4669 0.06836 0.06563 -0.0762 0.8537 0.0321
-12.000 -0.5097 0.05937 0.05648 -0.0802 0.8522 0.0317
-11.750 -0.7328 0.04661 0.04245 -0.0787 0.8581 0.0227
-11.500 -0.7508 0.04360 0.03918 -0.0749 0.8535 0.0226
-11.250 -0.7604 0.04083 0.03622 -0.0716 0.8493 0.0223
-11.000 -0.7705 0.03828 0.03342 -0.0675 0.8448 0.0222
-10.750 -0.7785 0.03575 0.03059 -0.0631 0.8409 0.0223
-10.500 -0.7758 0.03364 0.02819 -0.0602 0.8379 0.0223
-10.250 -0.7721 0.03212 0.02632 -0.0570 0.8349 0.0229
-10.000 -0.7622 0.03083 0.02479 -0.0548 0.8323 0.0231
-9.750 -0.7485 0.02835 0.02200 -0.0533 0.8298 0.0234
-9.500 -0.7229 0.02567 0.01917 -0.0540 0.8279 0.0239
-9.250 -0.7004 0.02454 0.01797 -0.0538 0.8257 0.0245
-9.000 -0.6784 0.02380 0.01719 -0.0534 0.8237 0.0252
-8.750 -0.6538 0.02275 0.01603 -0.0533 0.8219 0.0258
-8.500 -0.6289 0.02183 0.01499 -0.0532 0.8202 0.0265
-8.250 -0.6044 0.02111 0.01414 -0.0530 0.8184 0.0274
-8.000 -0.5819 0.02065 0.01359 -0.0524 0.8168 0.0281
-7.750 -0.5449 0.01900 0.01191 -0.0548 0.8156 0.0295
-7.500 -0.5192 0.01830 0.01123 -0.0549 0.8140 0.0305
-7.250 -0.4950 0.01770 0.01060 -0.0547 0.8122 0.0313
-7.000 -0.4723 0.01718 0.01007 -0.0542 0.8103 0.0323
-6.750 -0.4506 0.01676 0.00961 -0.0535 0.8085 0.0335
-6.500 -0.4293 0.01640 0.00919 -0.0526 0.8069 0.0343
-6.250 -0.4098 0.01583 0.00857 -0.0514 0.8055 0.0350
-6.000 -0.3956 0.01511 0.00783 -0.0494 0.8040 0.0364
-5.750 -0.3769 0.01474 0.00744 -0.0481 0.8026 0.0376
-5.500 -0.3567 0.01443 0.00713 -0.0470 0.8012 0.0393
-5.250 -0.3359 0.01412 0.00680 -0.0461 0.7999 0.0407
-5.000 -0.3142 0.01385 0.00651 -0.0453 0.7986 0.0421
-4.750 -0.2950 0.01345 0.00610 -0.0440 0.7971 0.0445
-4.500 -0.2735 0.01317 0.00583 -0.0432 0.7957 0.0477
-4.250 -0.2507 0.01295 0.00560 -0.0426 0.7944 0.0519
-4.000 -0.2302 0.01259 0.00533 -0.0415 0.7929 0.0672
-3.750 -0.2245 0.01142 0.00488 -0.0382 0.7911 0.2263
-3.500 -0.2238 0.01006 0.00442 -0.0340 0.7896 0.4376
-3.250 -0.2204 0.00902 0.00428 -0.0297 0.7882 0.6450
-3.000 -0.1955 0.00910 0.00442 -0.0291 0.7873 0.6946
-2.750 -0.1690 0.00923 0.00453 -0.0288 0.7864 0.7168
-2.500 -0.1423 0.00944 0.00474 -0.0286 0.7854 0.7338
-2.250 -0.1157 0.00966 0.00498 -0.0284 0.7844 0.7489
-2.000 -0.0890 0.00997 0.00533 -0.0280 0.7832 0.7637
-1.750 -0.0613 0.01027 0.00569 -0.0278 0.7819 0.7741
-1.500 -0.0345 0.01049 0.00591 -0.0276 0.7807 0.7830
-1.250 -0.0066 0.01080 0.00626 -0.0275 0.7796 0.7903
-1.000 0.0206 0.01094 0.00638 -0.0275 0.7781 0.7960
-0.750 0.0490 0.01081 0.00622 -0.0277 0.7750 0.7992
-0.500 0.0798 0.01044 0.00574 -0.0277 0.7686 0.8014
-0.250 0.1072 0.01033 0.00565 -0.0277 0.7636 0.8036
0.000 0.1355 0.01021 0.00551 -0.0279 0.7598 0.8056
0.250 0.1642 0.01017 0.00545 -0.0283 0.7578 0.8076
0.500 0.1934 0.01008 0.00533 -0.0287 0.7556 0.8096
0.750 0.2228 0.01003 0.00522 -0.0292 0.7534 0.8113
1.000 0.2503 0.00999 0.00521 -0.0295 0.7507 0.8130
1.250 0.2779 0.00988 0.00510 -0.0297 0.7462 0.8145
1.500 0.3070 0.00965 0.00485 -0.0301 0.7413 0.8158
1.750 0.3370 0.00950 0.00466 -0.0305 0.7373 0.8171
2.000 0.3637 0.00941 0.00464 -0.0305 0.7321 0.8186
2.250 0.3921 0.00927 0.00450 -0.0306 0.7261 0.8202
2.500 0.4217 0.00914 0.00434 -0.0310 0.7209 0.8218
2.750 0.4480 0.00906 0.00433 -0.0309 0.7145 0.8236
3.000 0.4761 0.00894 0.00422 -0.0311 0.7081 0.8254
3.250 0.5031 0.00885 0.00415 -0.0311 0.6995 0.8274
3.500 0.5299 0.00872 0.00402 -0.0310 0.6872 0.8296
3.750 0.5551 0.00863 0.00395 -0.0306 0.6682 0.8317
4.000 0.5753 0.00856 0.00375 -0.0291 0.6095 0.8337
4.250 0.5688 0.00950 0.00407 -0.0227 0.4856 0.8368
4.500 0.5613 0.01045 0.00459 -0.0165 0.3927 0.8405
4.750 0.5520 0.01119 0.00503 -0.0100 0.3222 0.8450
5.000 0.5451 0.01222 0.00567 -0.0044 0.2420 0.8492
5.250 0.5387 0.01339 0.00644 0.0007 0.1485 0.8535
5.500 0.5352 0.01465 0.00726 0.0053 0.0556 0.8583
5.750 0.5489 0.01524 0.00775 0.0071 0.0393 0.8625
6.000 0.5655 0.01571 0.00822 0.0085 0.0354 0.8661
6.250 0.5830 0.01609 0.00866 0.0098 0.0339 0.8697
6.500 0.6001 0.01653 0.00914 0.0112 0.0327 0.8738
6.750 0.6173 0.01699 0.00963 0.0124 0.0319 0.8784
7.000 0.6323 0.01757 0.01024 0.0139 0.0308 0.8831
7.250 0.6452 0.01821 0.01094 0.0158 0.0302 0.8880
7.500 0.6602 0.01879 0.01156 0.0173 0.0298 0.8937
7.750 0.6757 0.01935 0.01217 0.0187 0.0295 0.8994
8.000 0.6907 0.01987 0.01276 0.0203 0.0289 0.9054
8.250 0.7055 0.02047 0.01341 0.0218 0.0284 0.9126
8.500 0.7189 0.02108 0.01409 0.0235 0.0279 0.9201
8.750 0.7338 0.02164 0.01469 0.0250 0.0271 0.9294
9.000 0.7473 0.02226 0.01537 0.0266 0.0264 0.9400
9.250 0.7629 0.02302 0.01617 0.0277 0.0259 0.9526
9.500 0.7846 0.02404 0.01722 0.0274 0.0255 0.9647
9.750 0.8133 0.02494 0.01819 0.0258 0.0249 0.9753
10.000 0.8437 0.02575 0.01907 0.0240 0.0244 0.9902
10.250 0.8659 0.02654 0.01990 0.0240 0.0238 1.0000
10.500 0.8872 0.02732 0.02071 0.0243 0.0235 1.0000
10.750 0.9085 0.02812 0.02154 0.0245 0.0229 1.0000
11.000 0.9297 0.02892 0.02237 0.0248 0.0225 1.0000
11.250 0.9519 0.02981 0.02327 0.0250 0.0221 1.0000
11.500 0.9780 0.03082 0.02429 0.0248 0.0218 1.0000
11.750 1.0176 0.03245 0.02596 0.0231 0.0213 1.0000
12.000 1.0307 0.03365 0.02733 0.0243 0.0211 1.0000
12.250 1.0480 0.03516 0.02902 0.0250 0.0209 1.0000
12.500 1.0691 0.03725 0.03130 0.0252 0.0209 1.0000
12.750 1.0815 0.03927 0.03351 0.0263 0.0209 1.0000
13.000 1.0930 0.04171 0.03615 0.0273 0.0210 1.0000
13.250 1.1013 0.04459 0.03924 0.0285 0.0211 1.0000
13.500 1.1248 0.04808 0.04283 0.0280 0.0214 1.0000
13.750 0.9586 0.06675 0.06337 0.0418 0.0323 1.0000
14.000 0.9424 0.07034 0.06709 0.0426 0.0320 1.0000
14.250 0.9233 0.07450 0.07138 0.0429 0.0318 1.0000
14.500 0.8988 0.07950 0.07652 0.0425 0.0317 1.0000
14.750 0.8723 0.08530 0.08248 0.0410 0.0317 1.0000
15.000 0.8262 0.09485 0.09224 0.0368 0.0319 1.0000
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