NACA 66 (p51htip-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66 (p51htip-il) Reynolds number: 100,000 Max Cl/Cd: 38.74 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51htip-il-100000-n5.txt Download as CSV file: xf-p51htip-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4830 0.11034 0.10523 -0.0440 1.0000 0.0348
-11.500 -0.4793 0.10657 0.10145 -0.0447 1.0000 0.0340
-11.250 -0.4785 0.10228 0.09720 -0.0463 1.0000 0.0332
-11.000 -0.4815 0.09720 0.09216 -0.0490 1.0000 0.0328
-10.750 -0.4869 0.09160 0.08661 -0.0523 1.0000 0.0328
-10.500 -0.4939 0.08566 0.08073 -0.0563 1.0000 0.0324
-10.250 -0.5071 0.07923 0.07436 -0.0609 1.0000 0.0318
-10.000 -0.5275 0.07448 0.06961 -0.0628 1.0000 0.0316
-9.750 -0.5548 0.07150 0.06665 -0.0611 0.9982 0.0305
-9.500 -0.5651 0.06592 0.06087 -0.0651 0.9856 0.0301
-9.250 -0.5717 0.06143 0.05614 -0.0669 0.9748 0.0304
-9.000 -0.5736 0.05739 0.05183 -0.0675 0.9658 0.0310
-8.750 -0.5710 0.05334 0.04742 -0.0679 0.9593 0.0313
-8.500 -0.5699 0.04994 0.04370 -0.0666 0.9511 0.0312
-8.250 -0.5622 0.04629 0.03962 -0.0659 0.9459 0.0311
-8.000 -0.5575 0.04342 0.03637 -0.0637 0.9386 0.0310
-7.750 -0.5454 0.04048 0.03301 -0.0624 0.9336 0.0311
-7.500 -0.5337 0.03797 0.03007 -0.0606 0.9282 0.0313
-7.250 -0.5194 0.03572 0.02742 -0.0589 0.9230 0.0317
-7.000 -0.4995 0.03362 0.02489 -0.0580 0.9195 0.0328
-6.750 -0.4780 0.03207 0.02291 -0.0571 0.9163 0.0345
-6.500 -0.4602 0.03068 0.02114 -0.0555 0.9117 0.0357
-6.250 -0.4359 0.02858 0.01887 -0.0553 0.9088 0.0368
-6.000 -0.4095 0.02709 0.01727 -0.0554 0.9064 0.0381
-5.750 -0.3828 0.02606 0.01613 -0.0556 0.9042 0.0410
-5.500 -0.3576 0.02510 0.01502 -0.0553 0.9013 0.0437
-5.250 -0.3362 0.02423 0.01406 -0.0542 0.8974 0.0453
-5.000 -0.3134 0.02347 0.01320 -0.0534 0.8943 0.0469
-4.750 -0.2929 0.02258 0.01235 -0.0525 0.8917 0.0502
-4.500 -0.2708 0.02199 0.01171 -0.0518 0.8895 0.0548
-4.250 -0.2523 0.02156 0.01117 -0.0503 0.8865 0.0581
-4.000 -0.2380 0.02117 0.01074 -0.0481 0.8822 0.0619
-3.750 -0.2182 0.02080 0.01032 -0.0469 0.8790 0.0707
-3.500 -0.1970 0.02030 0.00989 -0.0459 0.8764 0.0873
-3.250 -0.1817 0.01918 0.00946 -0.0442 0.8743 0.2147
-3.000 -0.1893 0.01778 0.00942 -0.0385 0.8693 0.4944
-2.750 -0.1779 0.01806 0.01066 -0.0331 0.8663 0.7445
-2.500 -0.1594 0.01889 0.01150 -0.0293 0.8636 0.8064
-2.250 -0.1284 0.02023 0.01278 -0.0267 0.8626 0.8561
-2.000 -0.0853 0.02085 0.01324 -0.0284 0.8621 0.8732
-1.750 -0.0498 0.02095 0.01320 -0.0300 0.8609 0.8781
-1.500 -0.0286 0.02093 0.01305 -0.0290 0.8589 0.8861
-1.250 -0.0039 0.02113 0.01318 -0.0289 0.8553 0.8906
-1.000 0.0167 0.02126 0.01324 -0.0281 0.8519 0.8965
-0.750 0.0363 0.02130 0.01321 -0.0269 0.8488 0.9026
-0.500 0.0699 0.02134 0.01318 -0.0285 0.8471 0.9056
-0.250 0.1007 0.02136 0.01315 -0.0295 0.8453 0.9091
0.000 0.1085 0.02150 0.01327 -0.0263 0.8406 0.9164
0.250 0.1353 0.02166 0.01342 -0.0268 0.8370 0.9195
0.500 0.1638 0.02173 0.01348 -0.0274 0.8341 0.9228
0.750 0.1914 0.02176 0.01349 -0.0278 0.8317 0.9266
1.000 0.2173 0.02174 0.01348 -0.0277 0.8295 0.9310
1.250 0.2375 0.02205 0.01383 -0.0272 0.8238 0.9349
1.500 0.2638 0.02217 0.01398 -0.0275 0.8199 0.9385
1.750 0.2924 0.02218 0.01404 -0.0280 0.8170 0.9425
2.000 0.3244 0.02215 0.01407 -0.0290 0.8148 0.9456
2.250 0.3463 0.02249 0.01450 -0.0289 0.8079 0.9498
2.500 0.3774 0.02254 0.01464 -0.0300 0.8039 0.9528
2.750 0.4118 0.02245 0.01466 -0.0314 0.8010 0.9554
3.000 0.4335 0.02267 0.01500 -0.0309 0.7938 0.9606
3.250 0.4696 0.02259 0.01506 -0.0327 0.7888 0.9629
3.500 0.5100 0.02225 0.01489 -0.0347 0.7853 0.9644
3.750 0.5369 0.02200 0.01480 -0.0345 0.7737 0.9687
4.000 0.5828 0.01946 0.01236 -0.0340 0.7441 0.9682
4.250 0.6065 0.01783 0.01077 -0.0309 0.6923 0.9730
4.500 0.6380 0.01647 0.00868 -0.0286 0.5025 0.9748
4.750 0.6360 0.01850 0.00924 -0.0243 0.2574 0.9836
5.000 0.6481 0.02045 0.01011 -0.0232 0.0896 0.9900
5.250 0.6714 0.02137 0.01091 -0.0232 0.0666 0.9956
5.500 0.6918 0.02213 0.01169 -0.0226 0.0570 1.0000
5.750 0.6931 0.02259 0.01219 -0.0182 0.0533 1.0000
6.000 0.6910 0.02313 0.01274 -0.0133 0.0509 1.0000
6.250 0.6894 0.02360 0.01326 -0.0084 0.0493 1.0000
6.500 0.6904 0.02409 0.01381 -0.0039 0.0476 1.0000
6.750 0.6973 0.02473 0.01451 -0.0006 0.0450 1.0000
7.000 0.7088 0.02551 0.01531 0.0017 0.0421 1.0000
7.250 0.7240 0.02663 0.01638 0.0033 0.0398 1.0000
7.500 0.7499 0.02806 0.01782 0.0034 0.0383 1.0000
7.750 0.7817 0.02949 0.01941 0.0027 0.0369 1.0000
8.000 0.8104 0.03091 0.02101 0.0023 0.0349 1.0000
8.250 0.8355 0.03234 0.02259 0.0024 0.0328 1.0000
8.500 0.8611 0.03407 0.02449 0.0024 0.0317 1.0000
8.750 0.8848 0.03603 0.02665 0.0027 0.0308 1.0000
9.000 0.9057 0.03824 0.02908 0.0033 0.0302 1.0000
9.250 0.9234 0.04072 0.03183 0.0042 0.0297 1.0000
9.500 0.9374 0.04361 0.03500 0.0054 0.0292 1.0000
9.750 0.9440 0.04667 0.03838 0.0075 0.0286 1.0000
10.000 0.9450 0.04864 0.04076 0.0107 0.0279 1.0000
10.250 0.9433 0.05094 0.04343 0.0139 0.0273 1.0000
10.500 0.9372 0.05351 0.04632 0.0173 0.0270 1.0000
10.750 0.9288 0.05633 0.04941 0.0205 0.0269 1.0000
11.000 0.9174 0.05933 0.05268 0.0233 0.0269 1.0000
11.250 0.9036 0.06258 0.05617 0.0257 0.0269 1.0000
11.500 0.8884 0.06606 0.05988 0.0275 0.0269 1.0000
11.750 0.8697 0.07007 0.06410 0.0287 0.0270 1.0000
12.000 0.8502 0.07443 0.06865 0.0290 0.0270 1.0000
12.250 0.8308 0.07918 0.07356 0.0284 0.0272 1.0000
12.500 0.8088 0.08480 0.07933 0.0266 0.0273 1.0000
12.750 0.7872 0.09120 0.08586 0.0236 0.0275 1.0000
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Polar data table (+)
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