USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 27 AIRFOIL (usa27-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.37 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa27-il-1000000.txt Download as CSV file: xf-usa27-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2500 0.09472 0.09309 -0.0565 0.9926 0.0183
-9.250 -0.2414 0.08961 0.08798 -0.0614 0.9900 0.0184
-9.000 -0.2303 0.08459 0.08296 -0.0665 0.9877 0.0184
-8.750 -0.2233 0.07878 0.07715 -0.0717 0.9857 0.0187
-8.500 -0.2036 0.07581 0.07418 -0.0756 0.9844 0.0189
-8.250 -0.1879 0.07271 0.07108 -0.0794 0.9797 0.0191
-8.000 -0.1710 0.06892 0.06728 -0.0852 0.9742 0.0194
-7.750 -0.1555 0.06516 0.06349 -0.0901 0.9675 0.0198
-7.500 -0.1403 0.06122 0.05951 -0.0947 0.9595 0.0204
-7.250 -0.1238 0.05238 0.05052 -0.1045 0.9465 0.0224
-7.000 -0.1272 0.03779 0.03551 -0.1116 0.9326 0.0228
-6.750 -0.1116 0.03560 0.03325 -0.1116 0.9230 0.0230
-6.500 -0.0931 0.03375 0.03129 -0.1117 0.9139 0.0232
-6.250 -0.0752 0.03192 0.02935 -0.1115 0.9040 0.0235
-6.000 -0.0565 0.02994 0.02723 -0.1113 0.8951 0.0239
-5.750 -0.0377 0.02779 0.02488 -0.1109 0.8855 0.0245
-5.500 -0.0193 0.02543 0.02227 -0.1100 0.8757 0.0258
-5.250 0.0038 0.02462 0.02091 -0.1084 0.8663 0.0274
-5.000 0.0131 0.01993 0.01576 -0.1063 0.8563 0.0280
-4.750 0.0352 0.01857 0.01434 -0.1056 0.8468 0.0284
-4.500 0.0581 0.01760 0.01327 -0.1049 0.8363 0.0288
-4.250 0.0809 0.01675 0.01229 -0.1041 0.8244 0.0293
-4.000 0.1041 0.01597 0.01136 -0.1032 0.8118 0.0301
-3.750 0.1276 0.01528 0.01051 -0.1022 0.7983 0.0311
-3.500 0.1536 0.01566 0.01071 -0.1014 0.7822 0.0330
-3.250 0.1729 0.01374 0.00844 -0.0998 0.7636 0.0346
-3.000 0.1957 0.01305 0.00768 -0.0988 0.7384 0.0355
-2.750 0.2172 0.01267 0.00712 -0.0974 0.7040 0.0365
-2.500 0.2389 0.01244 0.00669 -0.0960 0.6728 0.0380
-2.250 0.2625 0.01255 0.00663 -0.0949 0.6514 0.0399
-1.750 0.3124 0.01100 0.00474 -0.0930 0.6248 0.0326
-1.500 0.3371 0.01033 0.00400 -0.0922 0.6146 0.0313
-1.250 0.3618 0.01006 0.00366 -0.0914 0.6045 0.0314
-1.000 0.3871 0.00973 0.00329 -0.0908 0.5947 0.0311
-0.750 0.4117 0.00949 0.00300 -0.0900 0.5840 0.0310
-0.500 0.4360 0.00933 0.00277 -0.0892 0.5707 0.0313
-0.250 0.4605 0.00921 0.00259 -0.0884 0.5559 0.0317
0.000 0.4851 0.00912 0.00244 -0.0877 0.5407 0.0321
0.250 0.5099 0.00906 0.00232 -0.0870 0.5247 0.0324
0.500 0.5344 0.00903 0.00222 -0.0863 0.5064 0.0328
0.750 0.5586 0.00905 0.00215 -0.0855 0.4859 0.0330
1.000 0.5826 0.00911 0.00212 -0.0847 0.4661 0.0333
1.500 0.6305 0.00918 0.00201 -0.0830 0.4329 0.0357
1.750 0.6550 0.00925 0.00201 -0.0824 0.4189 0.0373
2.000 0.6801 0.00931 0.00202 -0.0818 0.4077 0.0394
2.250 0.7052 0.00939 0.00206 -0.0813 0.3984 0.0448
2.500 0.7275 0.00910 0.00218 -0.0803 0.3900 0.2373
2.750 0.7514 0.00902 0.00233 -0.0797 0.3826 0.3403
3.250 0.8363 0.00811 0.00291 -0.0865 0.3674 0.9881
3.500 0.8902 0.00834 0.00308 -0.0925 0.3597 0.9949
3.750 0.9539 0.00853 0.00320 -0.1007 0.3516 0.9999
4.000 0.9779 0.00864 0.00329 -0.1000 0.3466 1.0000
4.250 0.9993 0.00878 0.00339 -0.0988 0.3412 1.0000
4.500 1.0212 0.00889 0.00349 -0.0976 0.3359 1.0000
4.750 1.0427 0.00902 0.00360 -0.0964 0.3292 1.0000
5.000 1.0632 0.00918 0.00372 -0.0950 0.3220 1.0000
5.250 1.0845 0.00930 0.00383 -0.0937 0.3149 1.0000
5.500 1.1042 0.00948 0.00397 -0.0921 0.3079 1.0000
5.750 1.1256 0.00959 0.00409 -0.0909 0.3026 1.0000
6.000 1.1450 0.00977 0.00423 -0.0893 0.2945 1.0000
6.250 1.1649 0.00993 0.00437 -0.0878 0.2847 1.0000
6.500 1.1832 0.01015 0.00453 -0.0859 0.2704 1.0000
6.750 1.2006 0.01042 0.00472 -0.0840 0.2536 1.0000
7.000 1.2151 0.01082 0.00498 -0.0815 0.2275 1.0000
7.250 1.2234 0.01152 0.00542 -0.0779 0.1864 1.0000
7.500 1.2344 0.01211 0.00586 -0.0749 0.1637 1.0000
7.750 1.2468 0.01255 0.00622 -0.0720 0.1484 1.0000
8.000 1.2566 0.01311 0.00663 -0.0687 0.1246 1.0000
8.250 1.2485 0.01468 0.00774 -0.0625 0.0556 1.0000
8.500 1.2519 0.01581 0.00871 -0.0585 0.0192 1.0000
8.750 1.2675 0.01631 0.00924 -0.0565 0.0169 1.0000
9.000 1.2838 0.01679 0.00976 -0.0548 0.0158 1.0000
9.250 1.2998 0.01728 0.01030 -0.0530 0.0150 1.0000
9.500 1.3150 0.01784 0.01091 -0.0512 0.0142 1.0000
9.750 1.3285 0.01850 0.01161 -0.0492 0.0135 1.0000
10.000 1.3389 0.01937 0.01255 -0.0468 0.0127 1.0000
10.250 1.3516 0.02011 0.01337 -0.0449 0.0124 1.0000
10.500 1.3650 0.02083 0.01413 -0.0431 0.0121 1.0000
10.750 1.3771 0.02163 0.01499 -0.0413 0.0117 1.0000
11.000 1.3884 0.02253 0.01594 -0.0394 0.0113 1.0000
11.250 1.3988 0.02349 0.01697 -0.0376 0.0109 1.0000
11.500 1.4080 0.02457 0.01810 -0.0358 0.0106 1.0000
11.750 1.4148 0.02587 0.01947 -0.0338 0.0102 1.0000
12.000 1.4157 0.02765 0.02134 -0.0315 0.0099 1.0000
12.250 1.4080 0.03023 0.02406 -0.0288 0.0096 1.0000
12.500 1.4145 0.03178 0.02568 -0.0274 0.0095 1.0000
12.750 1.4202 0.03347 0.02744 -0.0262 0.0094 1.0000
13.000 1.4238 0.03543 0.02949 -0.0251 0.0092 1.0000
13.250 1.4255 0.03769 0.03183 -0.0241 0.0090 1.0000
13.500 1.4255 0.04023 0.03446 -0.0233 0.0089 1.0000
13.750 1.4242 0.04308 0.03740 -0.0228 0.0087 1.0000
14.000 1.4219 0.04619 0.04061 -0.0225 0.0086 1.0000
14.250 1.4182 0.04958 0.04410 -0.0225 0.0085 1.0000
14.500 1.4138 0.05316 0.04777 -0.0226 0.0083 1.0000
14.750 1.4081 0.05697 0.05167 -0.0228 0.0082 1.0000
15.000 1.4014 0.06098 0.05579 -0.0233 0.0081 1.0000
15.250 1.3937 0.06517 0.06007 -0.0238 0.0081 1.0000
15.500 1.3859 0.06951 0.06451 -0.0245 0.0080 1.0000
15.750 1.3777 0.07397 0.06905 -0.0253 0.0079 1.0000
16.000 1.3690 0.07852 0.07369 -0.0262 0.0078 1.0000
16.250 1.3604 0.08315 0.07840 -0.0272 0.0077 1.0000
16.500 1.3520 0.08781 0.08314 -0.0283 0.0076 1.0000
16.750 1.3434 0.09249 0.08789 -0.0294 0.0076 1.0000
17.000 1.3343 0.09717 0.09264 -0.0305 0.0075 1.0000
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