NACA 747A415 (naca747a415-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 747A415 (naca747a415-il) Reynolds number: 100,000 Max Cl/Cd: 44.53 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca747a415-il-100000-n5.txt Download as CSV file: xf-naca747a415-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 747A415
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4126 0.12604 0.12101 -0.0315 1.0000 0.0466
-12.250 -0.4195 0.11317 0.10817 -0.0380 1.0000 0.0381
-12.000 -0.4177 0.10878 0.10381 -0.0400 1.0000 0.0379
-11.750 -0.4215 0.10318 0.09827 -0.0432 1.0000 0.0380
-11.500 -0.4295 0.09652 0.09166 -0.0475 1.0000 0.0382
-11.250 -0.4331 0.09101 0.08620 -0.0507 1.0000 0.0380
-11.000 -0.4419 0.08399 0.07923 -0.0557 1.0000 0.0378
-10.750 -0.4578 0.07600 0.07126 -0.0620 1.0000 0.0375
-10.500 -0.4734 0.06907 0.06422 -0.0683 0.9597 0.0371
-10.250 -0.4918 0.06261 0.05750 -0.0729 0.9313 0.0369
-10.000 -0.5086 0.05845 0.05308 -0.0729 0.9071 0.0368
-9.750 -0.5269 0.05520 0.04956 -0.0702 0.8879 0.0367
-9.500 -0.5403 0.05187 0.04590 -0.0674 0.8723 0.0367
-9.250 -0.5482 0.04866 0.04233 -0.0647 0.8585 0.0367
-9.000 -0.5515 0.04551 0.03876 -0.0619 0.8467 0.0370
-8.750 -0.5497 0.04267 0.03549 -0.0593 0.8369 0.0372
-8.500 -0.5469 0.03975 0.03196 -0.0565 0.8262 0.0381
-8.250 -0.5344 0.03781 0.02975 -0.0549 0.8174 0.0391
-8.000 -0.5176 0.03640 0.02820 -0.0538 0.8084 0.0401
-7.750 -0.5008 0.03471 0.02623 -0.0525 0.8005 0.0409
-7.500 -0.4826 0.03293 0.02412 -0.0512 0.7921 0.0416
-7.250 -0.4627 0.03124 0.02208 -0.0500 0.7852 0.0426
-7.000 -0.4407 0.02973 0.02025 -0.0491 0.7770 0.0439
-6.750 -0.4178 0.02841 0.01856 -0.0482 0.7707 0.0458
-6.500 -0.3934 0.02730 0.01743 -0.0480 0.7632 0.0475
-6.250 -0.3686 0.02626 0.01626 -0.0475 0.7568 0.0491
-6.000 -0.3432 0.02525 0.01508 -0.0470 0.7512 0.0509
-5.750 -0.3174 0.02440 0.01406 -0.0467 0.7442 0.0534
-5.500 -0.2933 0.02352 0.01318 -0.0461 0.7384 0.0563
-5.250 -0.2692 0.02282 0.01244 -0.0456 0.7325 0.0595
-5.000 -0.2453 0.02216 0.01169 -0.0449 0.7260 0.0628
-4.750 -0.2232 0.02148 0.01099 -0.0440 0.7208 0.0673
-4.500 -0.2005 0.02097 0.01043 -0.0432 0.7152 0.0732
-4.250 -0.1786 0.02042 0.00988 -0.0423 0.7093 0.0798
-4.000 -0.1559 0.01994 0.00936 -0.0414 0.7046 0.0901
-3.750 -0.1335 0.01944 0.00888 -0.0406 0.7003 0.1059
-3.500 -0.1115 0.01890 0.00855 -0.0398 0.6947 0.1387
-3.250 -0.0930 0.01799 0.00822 -0.0386 0.6900 0.2525
-3.000 -0.0843 0.01663 0.00794 -0.0355 0.6863 0.4882
-2.750 -0.0517 0.01706 0.00936 -0.0332 0.6822 0.7425
-2.250 -0.0124 0.01793 0.00999 -0.0284 0.6727 0.8186
-2.000 0.0320 0.01920 0.01113 -0.0283 0.6694 0.8614
-1.750 0.0809 0.01991 0.01168 -0.0305 0.6658 0.8876
-1.500 0.1212 0.02000 0.01164 -0.0330 0.6614 0.8939
-1.250 0.1526 0.01999 0.01151 -0.0339 0.6576 0.8991
-1.000 0.1748 0.01999 0.01139 -0.0330 0.6544 0.9064
-0.750 0.2156 0.01995 0.01119 -0.0356 0.6518 0.9105
-0.500 0.2460 0.02002 0.01121 -0.0364 0.6480 0.9167
-0.250 0.2706 0.02009 0.01123 -0.0362 0.6442 0.9224
0.000 0.3040 0.02007 0.01114 -0.0377 0.6406 0.9253
0.250 0.3333 0.02004 0.01104 -0.0383 0.6377 0.9287
0.500 0.3582 0.02003 0.01094 -0.0381 0.6353 0.9326
0.750 0.3791 0.02016 0.01108 -0.0373 0.6321 0.9365
1.000 0.4094 0.02028 0.01120 -0.0384 0.6286 0.9388
1.250 0.4382 0.02038 0.01129 -0.0392 0.6256 0.9414
1.500 0.4644 0.02046 0.01136 -0.0393 0.6229 0.9442
1.750 0.4883 0.02052 0.01141 -0.0389 0.6205 0.9475
2.000 0.5126 0.02057 0.01142 -0.0386 0.6184 0.9504
2.250 0.5404 0.02083 0.01176 -0.0394 0.6149 0.9525
2.500 0.5675 0.02111 0.01210 -0.0401 0.6117 0.9551
2.750 0.5928 0.02132 0.01235 -0.0402 0.6086 0.9578
3.000 0.6164 0.02147 0.01254 -0.0399 0.6059 0.9607
3.250 0.6422 0.02159 0.01268 -0.0399 0.6036 0.9633
3.500 0.6729 0.02166 0.01276 -0.0408 0.6016 0.9650
3.750 0.6951 0.02219 0.01344 -0.0409 0.5968 0.9677
4.000 0.7187 0.02253 0.01388 -0.0409 0.5929 0.9705
4.250 0.7429 0.02273 0.01415 -0.0407 0.5897 0.9736
4.500 0.7726 0.02280 0.01427 -0.0414 0.5870 0.9755
4.750 0.8020 0.02291 0.01445 -0.0421 0.5845 0.9773
5.000 0.8205 0.02367 0.01541 -0.0418 0.5786 0.9808
5.250 0.8440 0.02397 0.01582 -0.0417 0.5745 0.9837
5.500 0.8739 0.02401 0.01594 -0.0424 0.5713 0.9859
5.750 0.9059 0.02395 0.01596 -0.0433 0.5681 0.9879
6.000 0.9238 0.02468 0.01691 -0.0430 0.5600 0.9923
6.250 0.9551 0.02431 0.01660 -0.0433 0.5546 0.9943
6.500 0.9786 0.02455 0.01703 -0.0433 0.5468 0.9978
6.750 1.0079 0.02418 0.01674 -0.0434 0.5390 1.0000
7.000 1.0157 0.02427 0.01694 -0.0401 0.5295 1.0000
7.250 1.0384 0.02354 0.01624 -0.0384 0.5187 1.0000
7.500 1.0438 0.02344 0.01623 -0.0346 0.5061 1.0000
7.750 1.0394 0.02367 0.01657 -0.0294 0.4942 1.0000
8.000 1.0353 0.02369 0.01664 -0.0241 0.4806 1.0000
8.250 1.0271 0.02384 0.01684 -0.0183 0.4664 1.0000
8.500 1.0148 0.02434 0.01737 -0.0125 0.4508 1.0000
9.000 0.9918 0.02693 0.02007 -0.0044 0.4089 1.0000
9.250 1.0052 0.02696 0.01989 -0.0024 0.3641 1.0000
9.500 1.0078 0.02788 0.02040 0.0002 0.3147 1.0000
9.750 0.9997 0.02997 0.02221 0.0026 0.2742 1.0000
10.000 0.9892 0.03253 0.02453 0.0047 0.2362 1.0000
10.250 0.9791 0.03527 0.02705 0.0064 0.2020 1.0000
10.500 0.9714 0.03799 0.02957 0.0077 0.1707 1.0000
10.750 0.9654 0.04067 0.03208 0.0088 0.1409 1.0000
11.000 0.9617 0.04324 0.03448 0.0098 0.1149 1.0000
11.250 0.9596 0.04574 0.03682 0.0106 0.0934 1.0000
11.500 0.9608 0.04801 0.03900 0.0113 0.0794 1.0000
11.750 0.9627 0.05030 0.04124 0.0119 0.0684 1.0000
12.000 0.9657 0.05256 0.04346 0.0123 0.0616 1.0000
12.250 0.9701 0.05472 0.04567 0.0127 0.0560 1.0000
12.500 0.9743 0.05694 0.04791 0.0130 0.0519 1.0000
12.750 0.9796 0.05911 0.05012 0.0132 0.0482 1.0000
13.000 0.9836 0.06142 0.05243 0.0134 0.0456 1.0000
13.250 0.9909 0.06341 0.05453 0.0136 0.0430 1.0000
13.500 0.9974 0.06553 0.05670 0.0137 0.0409 1.0000
13.750 1.0032 0.06772 0.05890 0.0138 0.0392 1.0000
14.000 1.0123 0.06957 0.06085 0.0140 0.0374 1.0000
14.250 1.0212 0.07149 0.06287 0.0142 0.0356 1.0000
14.500 1.0305 0.07338 0.06482 0.0143 0.0344 1.0000
14.750 1.0402 0.07520 0.06666 0.0145 0.0334 1.0000
15.000 1.0525 0.07674 0.06819 0.0149 0.0325 1.0000
15.250 1.0621 0.07884 0.07050 0.0151 0.0314 1.0000
15.500 1.0709 0.08106 0.07290 0.0150 0.0306 1.0000
15.750 1.0768 0.08369 0.07569 0.0147 0.0296 1.0000
16.000 1.0818 0.08644 0.07858 0.0142 0.0288 1.0000
16.250 1.0856 0.08931 0.08153 0.0135 0.0281 1.0000
16.500 1.0915 0.09198 0.08431 0.0131 0.0276 1.0000
16.750 1.0976 0.09469 0.08707 0.0126 0.0271 1.0000
17.000 1.0934 0.09901 0.09166 0.0113 0.0269 1.0000
17.250 1.0872 0.10374 0.09665 0.0096 0.0267 1.0000
17.500 1.0780 0.10902 0.10220 0.0074 0.0265 1.0000
17.750 1.0659 0.11496 0.10839 0.0047 0.0264 1.0000
18.000 1.0515 0.12151 0.11519 0.0014 0.0263 1.0000
18.250 1.0357 0.12864 0.12255 -0.0025 0.0263 1.0000
18.500 1.0151 0.13715 0.13130 -0.0075 0.0264 1.0000
18.750 0.9901 0.14728 0.14166 -0.0137 0.0265 1.0000
19.000 0.9609 0.15941 0.15398 -0.0213 0.0267 1.0000
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