NACA 64-108 AIRFOIL (n64108-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-108 AIRFOIL (n64108-il) Reynolds number: 200,000 Max Cl/Cd: 43.49 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64108-il-200000-n5.txt Download as CSV file: xf-n64108-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-108 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6240 0.08622 0.08276 -0.0063 1.0000 0.0118
-9.000 -0.6294 0.08020 0.07679 -0.0107 1.0000 0.0117
-8.750 -0.6397 0.07303 0.06965 -0.0175 1.0000 0.0116
-8.500 -0.6531 0.06764 0.06425 -0.0213 1.0000 0.0114
-8.250 -0.6608 0.06218 0.05867 -0.0237 1.0000 0.0111
-8.000 -0.6640 0.05679 0.05310 -0.0252 1.0000 0.0112
-7.750 -0.6631 0.05143 0.04750 -0.0260 1.0000 0.0112
-7.500 -0.6578 0.04636 0.04213 -0.0261 1.0000 0.0112
-7.250 -0.6471 0.04208 0.03749 -0.0259 1.0000 0.0121
-7.000 -0.6338 0.03767 0.03265 -0.0253 1.0000 0.0132
-6.750 -0.6187 0.03348 0.02799 -0.0244 1.0000 0.0137
-6.500 -0.6014 0.02978 0.02379 -0.0234 1.0000 0.0140
-6.250 -0.5813 0.02696 0.02049 -0.0225 1.0000 0.0144
-6.000 -0.5614 0.02366 0.01671 -0.0216 1.0000 0.0151
-5.750 -0.5399 0.02175 0.01461 -0.0211 1.0000 0.0165
-5.500 -0.5166 0.02093 0.01367 -0.0207 1.0000 0.0185
-5.250 -0.4932 0.01944 0.01196 -0.0199 1.0000 0.0198
-5.000 -0.4700 0.01804 0.01038 -0.0189 1.0000 0.0209
-4.750 -0.4473 0.01690 0.00907 -0.0180 1.0000 0.0221
-4.500 -0.4245 0.01635 0.00841 -0.0171 1.0000 0.0238
-4.250 -0.4044 0.01505 0.00707 -0.0159 1.0000 0.0255
-4.000 -0.3816 0.01409 0.00608 -0.0153 0.9984 0.0271
-3.750 -0.3477 0.01331 0.00524 -0.0169 0.9902 0.0300
-3.500 -0.3134 0.01271 0.00450 -0.0186 0.9823 0.0342
-3.250 -0.2791 0.01213 0.00388 -0.0202 0.9742 0.0425
-3.000 -0.2453 0.01163 0.00339 -0.0218 0.9657 0.0605
-2.750 -0.2152 0.01039 0.00288 -0.0233 0.9557 0.2245
-2.500 -0.1885 0.00902 0.00261 -0.0240 0.9453 0.5097
-2.250 -0.1587 0.00870 0.00256 -0.0244 0.9355 0.5998
-2.000 -0.1332 0.00846 0.00273 -0.0233 0.9248 0.7075
-1.750 -0.1078 0.00842 0.00281 -0.0222 0.9132 0.7582
-1.500 -0.0802 0.00839 0.00272 -0.0220 0.9020 0.7734
-1.000 -0.0256 0.00833 0.00257 -0.0213 0.8800 0.7961
-0.750 0.0011 0.00831 0.00252 -0.0208 0.8693 0.8071
-0.500 0.0273 0.00830 0.00247 -0.0203 0.8579 0.8185
-0.250 0.0536 0.00829 0.00245 -0.0198 0.8469 0.8300
0.000 0.0797 0.00829 0.00243 -0.0192 0.8362 0.8419
0.250 0.1056 0.00829 0.00243 -0.0186 0.8257 0.8538
0.500 0.1314 0.00829 0.00245 -0.0180 0.8151 0.8656
0.750 0.1573 0.00830 0.00248 -0.0173 0.8042 0.8779
1.000 0.1834 0.00831 0.00251 -0.0168 0.7937 0.8906
1.250 0.2100 0.00833 0.00256 -0.0163 0.7839 0.9037
1.500 0.2374 0.00835 0.00263 -0.0160 0.7733 0.9172
1.750 0.2659 0.00837 0.00270 -0.0160 0.7616 0.9309
2.000 0.2953 0.00840 0.00273 -0.0161 0.7444 0.9448
2.250 0.3251 0.00842 0.00268 -0.0161 0.7048 0.9586
2.500 0.3546 0.00861 0.00257 -0.0161 0.6209 0.9734
2.750 0.3866 0.00889 0.00260 -0.0170 0.5464 0.9902
3.000 0.4105 0.00952 0.00272 -0.0166 0.4116 1.0000
3.250 0.4252 0.01137 0.00328 -0.0155 0.1354 1.0000
3.500 0.4476 0.01230 0.00382 -0.0150 0.0563 1.0000
3.750 0.4724 0.01285 0.00432 -0.0147 0.0413 1.0000
4.000 0.4976 0.01340 0.00495 -0.0144 0.0355 1.0000
4.250 0.5224 0.01401 0.00564 -0.0140 0.0314 1.0000
4.500 0.5461 0.01485 0.00652 -0.0135 0.0284 1.0000
4.750 0.5693 0.01582 0.00754 -0.0129 0.0258 1.0000
5.000 0.5940 0.01655 0.00840 -0.0125 0.0238 1.0000
5.250 0.6181 0.01758 0.00952 -0.0119 0.0224 1.0000
5.500 0.6424 0.01876 0.01081 -0.0113 0.0211 1.0000
5.750 0.6669 0.02011 0.01229 -0.0107 0.0200 1.0000
6.000 0.6914 0.02126 0.01355 -0.0104 0.0185 1.0000
6.250 0.7132 0.02380 0.01626 -0.0098 0.0165 1.0000
6.500 0.7373 0.02540 0.01821 -0.0092 0.0159 1.0000
6.750 0.7598 0.02765 0.02087 -0.0084 0.0153 1.0000
7.000 0.7800 0.03063 0.02432 -0.0073 0.0147 1.0000
7.250 0.7988 0.03353 0.02766 -0.0062 0.0134 1.0000
7.500 0.8171 0.03569 0.03013 -0.0055 0.0120 1.0000
7.750 0.8313 0.03887 0.03367 -0.0045 0.0115 1.0000
8.000 0.8420 0.04245 0.03761 -0.0035 0.0111 1.0000
8.250 0.8491 0.04633 0.04182 -0.0026 0.0108 1.0000
8.500 0.8508 0.05093 0.04675 -0.0016 0.0107 1.0000
8.750 0.8474 0.05581 0.05193 -0.0008 0.0106 1.0000
9.000 0.8384 0.06112 0.05749 -0.0004 0.0107 1.0000
9.250 0.8220 0.06614 0.06269 0.0000 0.0108 1.0000
9.500 0.7951 0.07328 0.06998 -0.0026 0.0112 1.0000
9.750 0.7736 0.08190 0.07867 -0.0093 0.0115 1.0000
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Polar data table (+)
Polar graphs
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