GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GM15 (smoothed) (gm15sm-il) Reynolds number: 200,000 Max Cl/Cd: 91.52 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-gm15sm-il-200000.txt Download as CSV file: xf-gm15sm-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GM15 (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3535 0.09956 0.09621 -0.0283 1.0000 0.0359
-7.500 -0.3635 0.09830 0.09503 -0.0262 1.0000 0.0360
-7.250 -0.3686 0.09644 0.09322 -0.0254 1.0000 0.0361
-7.000 -0.3701 0.09412 0.09096 -0.0255 1.0000 0.0362
-6.750 -0.3699 0.09154 0.08841 -0.0262 1.0000 0.0362
-6.500 -0.3764 0.08628 0.08322 -0.0219 1.0000 0.0376
-6.250 -0.3737 0.08426 0.08122 -0.0190 1.0000 0.0389
-6.000 -0.3716 0.08237 0.07936 -0.0176 1.0000 0.0412
-5.750 -0.3696 0.07996 0.07698 -0.0181 1.0000 0.0429
-5.500 -0.3644 0.07712 0.07417 -0.0205 1.0000 0.0455
-5.250 -0.3343 0.07237 0.06938 -0.0355 1.0000 0.0484
-5.000 -0.3138 0.06568 0.06267 -0.0425 0.9989 0.0494
-4.750 -0.2943 0.06280 0.05980 -0.0420 0.9955 0.0512
-4.500 -0.2606 0.05920 0.05616 -0.0472 0.9912 0.0544
-4.250 -0.1850 0.04861 0.04525 -0.0708 0.9878 0.0632
-4.000 -0.1570 0.04667 0.04331 -0.0720 0.9836 0.0659
-3.750 -0.0957 0.03882 0.03508 -0.0867 0.9803 0.0775
-3.500 -0.0228 0.02377 0.01823 -0.1000 0.9825 0.0353
-3.250 0.0181 0.02046 0.01428 -0.1031 0.9798 0.0347
-3.000 0.0585 0.01824 0.01155 -0.1058 0.9770 0.0386
-2.750 0.0990 0.01680 0.00988 -0.1082 0.9740 0.0410
-2.500 0.1347 0.01572 0.00863 -0.1094 0.9682 0.0456
-2.250 0.1753 0.01470 0.00756 -0.1119 0.9643 0.0563
-2.000 0.2162 0.01383 0.00672 -0.1144 0.9603 0.0868
-1.750 0.2526 0.01314 0.00644 -0.1162 0.9536 0.2054
-1.500 0.2963 0.01303 0.00632 -0.1193 0.9495 0.2574
-1.250 0.3321 0.01295 0.00626 -0.1208 0.9419 0.2923
-1.000 0.3751 0.01274 0.00604 -0.1236 0.9373 0.3251
-0.750 0.4165 0.01246 0.00578 -0.1261 0.9320 0.3518
-0.500 0.4558 0.01216 0.00555 -0.1282 0.9251 0.3774
-0.250 0.5006 0.01178 0.00523 -0.1313 0.9211 0.4065
0.000 0.5318 0.01151 0.00505 -0.1316 0.9103 0.4330
0.250 0.5648 0.01119 0.00483 -0.1323 0.9002 0.4648
0.500 0.5993 0.01078 0.00458 -0.1332 0.8906 0.5059
0.750 0.6309 0.01025 0.00434 -0.1335 0.8797 0.5794
1.000 0.6678 0.00930 0.00406 -0.1347 0.8667 1.0000
1.250 0.6972 0.00921 0.00387 -0.1345 0.8511 1.0000
1.500 0.7250 0.00916 0.00374 -0.1340 0.8327 1.0000
1.750 0.7541 0.00912 0.00361 -0.1337 0.8140 1.0000
2.000 0.7825 0.00914 0.00356 -0.1334 0.7936 1.0000
2.250 0.8103 0.00921 0.00353 -0.1329 0.7719 1.0000
2.500 0.8370 0.00935 0.00356 -0.1323 0.7494 1.0000
2.750 0.8637 0.00953 0.00363 -0.1316 0.7276 1.0000
3.000 0.8889 0.00975 0.00380 -0.1308 0.7048 1.0000
3.250 0.9143 0.01000 0.00396 -0.1300 0.6835 1.0000
3.500 0.9390 0.01026 0.00416 -0.1291 0.6616 1.0000
3.750 0.9636 0.01054 0.00438 -0.1282 0.6408 1.0000
4.000 0.9879 0.01082 0.00463 -0.1272 0.6195 1.0000
4.250 1.0121 0.01112 0.00494 -0.1263 0.5984 1.0000
4.500 1.0359 0.01143 0.00523 -0.1253 0.5766 1.0000
4.750 1.0587 0.01173 0.00551 -0.1240 0.5507 1.0000
5.000 1.0786 0.01206 0.00570 -0.1221 0.5097 1.0000
5.250 1.0975 0.01249 0.00594 -0.1202 0.4622 1.0000
5.500 1.1174 0.01296 0.00627 -0.1186 0.4186 1.0000
5.750 1.1365 0.01353 0.00672 -0.1169 0.3680 1.0000
6.000 1.1526 0.01441 0.00726 -0.1147 0.2945 1.0000
6.250 1.1529 0.01727 0.00869 -0.1108 0.0847 1.0000
6.500 1.1653 0.01913 0.01032 -0.1081 0.0474 1.0000
6.750 1.1800 0.02058 0.01185 -0.1057 0.0406 1.0000
7.000 1.1959 0.02182 0.01320 -0.1035 0.0367 1.0000
7.250 1.2089 0.02342 0.01482 -0.1011 0.0327 1.0000
7.500 1.2228 0.02533 0.01684 -0.0987 0.0304 1.0000
7.750 1.2416 0.02694 0.01857 -0.0970 0.0290 1.0000
8.000 1.2624 0.02890 0.02065 -0.0956 0.0277 1.0000
8.250 1.2829 0.03064 0.02252 -0.0943 0.0255 1.0000
8.500 1.3018 0.03268 0.02460 -0.0932 0.0231 1.0000
8.750 1.3251 0.03638 0.02852 -0.0925 0.0223 1.0000
9.000 1.3449 0.04002 0.03248 -0.0912 0.0222 1.0000
9.250 1.3610 0.04294 0.03575 -0.0892 0.0225 1.0000
9.500 1.3690 0.04756 0.04124 -0.0850 0.0257 1.0000
9.750 1.3688 0.05407 0.04828 -0.0816 0.0293 1.0000
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Polar data table (+)
Polar graphs
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