NACA 64-108 AIRFOIL (n64108-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-108 AIRFOIL (n64108-il) Reynolds number: 1,000,000 Max Cl/Cd: 65.29 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64108-il-1000000-n5.txt Download as CSV file: xf-n64108-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6559 0.11117 0.10955 0.0095 1.0000 0.0031
-9.750 -0.9314 0.02430 0.02090 -0.0230 1.0000 0.0028
-9.500 -0.9156 0.02171 0.01796 -0.0223 1.0000 0.0028
-9.250 -0.8951 0.02023 0.01627 -0.0218 1.0000 0.0029
-9.000 -0.8777 0.01777 0.01344 -0.0210 1.0000 0.0032
-8.750 -0.8539 0.01703 0.01262 -0.0207 1.0000 0.0035
-8.500 -0.8294 0.01649 0.01201 -0.0205 1.0000 0.0038
-8.250 -0.8051 0.01581 0.01124 -0.0202 1.0000 0.0040
-8.000 -0.7805 0.01520 0.01051 -0.0200 1.0000 0.0043
-7.750 -0.7564 0.01440 0.00960 -0.0196 1.0000 0.0046
-7.500 -0.7320 0.01368 0.00876 -0.0193 1.0000 0.0049
-7.250 -0.7072 0.01308 0.00807 -0.0190 1.0000 0.0051
-7.000 -0.6825 0.01246 0.00736 -0.0186 1.0000 0.0053
-6.750 -0.6581 0.01180 0.00664 -0.0183 1.0000 0.0060
-6.500 -0.6274 0.01152 0.00635 -0.0192 0.9908 0.0065
-6.250 -0.5944 0.01120 0.00598 -0.0206 0.9791 0.0073
-6.000 -0.5617 0.01092 0.00566 -0.0219 0.9668 0.0081
-5.750 -0.5315 0.01065 0.00534 -0.0226 0.9528 0.0086
-5.500 -0.5045 0.01040 0.00503 -0.0226 0.9375 0.0088
-5.250 -0.4803 0.00965 0.00412 -0.0220 0.9223 0.0100
-5.000 -0.4547 0.00935 0.00376 -0.0216 0.9085 0.0109
-4.750 -0.4285 0.00916 0.00350 -0.0213 0.8955 0.0118
-4.250 -0.3757 0.00869 0.00288 -0.0208 0.8709 0.0131
-4.000 -0.3489 0.00846 0.00257 -0.0207 0.8594 0.0136
-3.750 -0.3219 0.00829 0.00233 -0.0206 0.8483 0.0143
-3.500 -0.2948 0.00807 0.00202 -0.0204 0.8376 0.0156
-3.250 -0.2677 0.00787 0.00179 -0.0203 0.8269 0.0199
-3.000 -0.2402 0.00774 0.00163 -0.0203 0.8166 0.0234
-2.750 -0.2126 0.00762 0.00147 -0.0203 0.8067 0.0276
-2.500 -0.1851 0.00750 0.00132 -0.0203 0.7965 0.0342
-2.250 -0.1576 0.00737 0.00120 -0.0203 0.7860 0.0458
-2.000 -0.1302 0.00714 0.00107 -0.0203 0.7755 0.0836
-1.750 -0.1032 0.00674 0.00092 -0.0204 0.7659 0.1676
-1.500 -0.0771 0.00605 0.00073 -0.0206 0.7562 0.3298
-1.250 -0.0507 0.00551 0.00061 -0.0207 0.7460 0.4667
-1.000 -0.0237 0.00520 0.00058 -0.0208 0.7358 0.5562
-0.750 0.0035 0.00502 0.00057 -0.0207 0.7261 0.6191
-0.500 0.0310 0.00492 0.00056 -0.0207 0.7167 0.6577
-0.250 0.0588 0.00486 0.00057 -0.0207 0.7076 0.6854
0.000 0.0869 0.00486 0.00057 -0.0207 0.6982 0.6982
0.250 0.1147 0.00489 0.00058 -0.0207 0.6799 0.7084
0.500 0.1422 0.00497 0.00058 -0.0207 0.6527 0.7178
0.750 0.1699 0.00504 0.00060 -0.0207 0.6314 0.7277
1.000 0.1974 0.00513 0.00063 -0.0206 0.6020 0.7379
1.250 0.2241 0.00535 0.00067 -0.0205 0.5437 0.7481
1.500 0.2507 0.00563 0.00075 -0.0204 0.4771 0.7584
1.750 0.2753 0.00635 0.00093 -0.0202 0.3228 0.7686
2.000 0.2999 0.00712 0.00118 -0.0200 0.1703 0.7786
2.250 0.3262 0.00752 0.00136 -0.0200 0.0980 0.7893
2.500 0.3528 0.00784 0.00155 -0.0199 0.0519 0.8004
2.750 0.3800 0.00801 0.00170 -0.0199 0.0368 0.8114
3.000 0.4072 0.00816 0.00185 -0.0198 0.0303 0.8220
3.250 0.4344 0.00829 0.00203 -0.0197 0.0260 0.8329
3.500 0.4614 0.00844 0.00222 -0.0196 0.0212 0.8443
3.750 0.4881 0.00866 0.00246 -0.0194 0.0163 0.8561
4.000 0.5147 0.00883 0.00269 -0.0192 0.0153 0.8684
4.250 0.5410 0.00902 0.00295 -0.0189 0.0143 0.8813
4.500 0.5669 0.00923 0.00323 -0.0185 0.0135 0.8951
4.750 0.5923 0.00946 0.00354 -0.0181 0.0127 0.9096
5.000 0.6172 0.00973 0.00387 -0.0175 0.0117 0.9254
5.250 0.6407 0.01020 0.00446 -0.0167 0.0102 0.9435
5.500 0.6668 0.01063 0.00499 -0.0164 0.0098 0.9659
5.750 0.6987 0.01099 0.00541 -0.0176 0.0095 1.0000
6.000 0.7251 0.01132 0.00579 -0.0175 0.0090 1.0000
6.250 0.7516 0.01163 0.00613 -0.0174 0.0083 1.0000
6.500 0.7777 0.01201 0.00655 -0.0173 0.0077 1.0000
6.750 0.8038 0.01237 0.00693 -0.0172 0.0072 1.0000
7.000 0.8298 0.01271 0.00729 -0.0171 0.0067 1.0000
7.250 0.8537 0.01354 0.00820 -0.0167 0.0060 1.0000
7.500 0.8786 0.01411 0.00884 -0.0164 0.0057 1.0000
7.750 0.9041 0.01454 0.00937 -0.0163 0.0054 1.0000
8.000 0.9293 0.01498 0.00987 -0.0161 0.0050 1.0000
8.250 0.9547 0.01539 0.01031 -0.0159 0.0046 1.0000
8.500 0.9797 0.01582 0.01079 -0.0157 0.0042 1.0000
8.750 1.0045 0.01629 0.01130 -0.0155 0.0039 1.0000
9.000 1.0282 0.01699 0.01207 -0.0152 0.0036 1.0000
9.250 1.0489 0.01834 0.01360 -0.0145 0.0033 1.0000
9.500 1.0714 0.01925 0.01465 -0.0140 0.0032 1.0000
9.750 1.0925 0.02041 0.01599 -0.0134 0.0031 1.0000
10.000 1.1131 0.02161 0.01739 -0.0127 0.0029 1.0000
10.250 1.1317 0.02315 0.01915 -0.0119 0.0028 1.0000
10.500 1.1492 0.02478 0.02099 -0.0111 0.0027 1.0000
10.750 1.1651 0.02659 0.02303 -0.0101 0.0026 1.0000
11.000 1.1767 0.02904 0.02577 -0.0088 0.0025 1.0000
11.250 1.1871 0.03142 0.02841 -0.0076 0.0024 1.0000
11.500 1.1804 0.03641 0.03385 -0.0053 0.0023 1.0000
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Polar data table (+)
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