NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.84 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ames03-il-1000000.txt Download as CSV file: xf-ames03-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/AMES A-03 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5678 0.11183 0.11018 0.0289 0.8460 0.0144
-10.250 -1.0078 0.04381 0.04125 0.0076 0.8523 0.0089
-10.000 -1.0423 0.03276 0.02925 0.0101 0.8499 0.0091
-9.750 -1.0360 0.02844 0.02448 0.0114 0.8478 0.0094
-9.500 -1.0139 0.02750 0.02346 0.0117 0.8458 0.0097
-9.250 -0.9898 0.02700 0.02290 0.0119 0.8438 0.0099
-9.000 -0.9669 0.02605 0.02183 0.0122 0.8420 0.0102
-8.750 -0.9441 0.02489 0.02052 0.0125 0.8402 0.0105
-8.500 -0.9217 0.02339 0.01881 0.0130 0.8383 0.0107
-8.250 -0.8980 0.02197 0.01718 0.0133 0.8365 0.0110
-8.000 -0.8734 0.02059 0.01561 0.0135 0.8347 0.0113
-7.750 -0.8479 0.01946 0.01431 0.0137 0.8329 0.0115
-7.500 -0.8218 0.01852 0.01323 0.0138 0.8311 0.0118
-7.250 -0.7950 0.01786 0.01245 0.0139 0.8293 0.0120
-7.000 -0.7709 0.01593 0.01030 0.0143 0.8277 0.0126
-6.750 -0.7442 0.01522 0.00954 0.0143 0.8261 0.0131
-6.500 -0.7165 0.01489 0.00918 0.0142 0.8245 0.0137
-6.250 -0.6889 0.01443 0.00866 0.0142 0.8227 0.0143
-6.000 -0.6607 0.01389 0.00806 0.0141 0.8211 0.0148
-5.750 -0.6324 0.01343 0.00756 0.0139 0.8195 0.0153
-5.500 -0.6038 0.01304 0.00712 0.0137 0.8178 0.0158
-5.250 -0.5762 0.01218 0.00618 0.0137 0.8162 0.0167
-5.000 -0.5478 0.01172 0.00570 0.0135 0.8145 0.0177
-4.750 -0.5193 0.01142 0.00538 0.0133 0.8123 0.0187
-4.500 -0.4909 0.01114 0.00506 0.0133 0.8099 0.0198
-4.250 -0.4622 0.01100 0.00488 0.0131 0.8074 0.0207
-4.000 -0.4331 0.01042 0.00429 0.0128 0.8051 0.0233
-3.750 -0.4039 0.01017 0.00404 0.0126 0.8022 0.0253
-3.500 -0.3746 0.00998 0.00382 0.0123 0.7999 0.0268
-3.250 -0.3455 0.00963 0.00348 0.0121 0.7976 0.0318
-3.000 -0.3165 0.00941 0.00324 0.0119 0.7950 0.0364
-2.750 -0.2875 0.00921 0.00304 0.0117 0.7922 0.0438
-2.500 -0.2577 0.00891 0.00285 0.0113 0.7897 0.0624
-2.250 -0.2281 0.00861 0.00269 0.0108 0.7870 0.0951
-2.000 -0.1988 0.00822 0.00252 0.0104 0.7840 0.1549
-1.750 -0.1697 0.00773 0.00234 0.0099 0.7806 0.2433
-1.500 -0.1406 0.00697 0.00215 0.0092 0.7767 0.4085
-1.250 -0.1108 0.00619 0.00202 0.0083 0.7723 0.5882
-1.000 -0.0816 0.00579 0.00192 0.0081 0.7666 0.6850
-0.750 -0.0526 0.00557 0.00187 0.0079 0.7603 0.7435
-0.500 -0.0237 0.00539 0.00185 0.0079 0.7534 0.7914
-0.250 0.0051 0.00533 0.00181 0.0079 0.7478 0.8180
0.000 0.0341 0.00524 0.00181 0.0078 0.7406 0.8423
0.250 0.0627 0.00520 0.00178 0.0079 0.7321 0.8641
0.500 0.0915 0.00517 0.00177 0.0079 0.7215 0.8788
0.750 0.1197 0.00515 0.00176 0.0081 0.7079 0.8972
1.000 0.1471 0.00515 0.00174 0.0084 0.6870 0.9139
1.250 0.1766 0.00532 0.00169 0.0082 0.6154 0.9242
1.500 0.2149 0.00656 0.00196 0.0047 0.3668 0.9298
1.750 0.2450 0.00695 0.00207 0.0039 0.2970 0.9368
2.000 0.2742 0.00715 0.00215 0.0034 0.2679 0.9440
2.250 0.3017 0.00727 0.00220 0.0035 0.2521 0.9516
2.500 0.3296 0.00739 0.00226 0.0035 0.2401 0.9593
2.750 0.3565 0.00745 0.00230 0.0037 0.2325 0.9680
3.000 0.3848 0.00755 0.00235 0.0036 0.2247 0.9766
3.250 0.4153 0.00761 0.00240 0.0030 0.2193 0.9852
3.500 0.4486 0.00774 0.00249 0.0016 0.2123 0.9926
3.750 0.4819 0.00784 0.00258 0.0003 0.2070 1.0000
4.000 0.5126 0.00797 0.00269 -0.0005 0.2018 1.0000
4.250 0.5433 0.00816 0.00283 -0.0014 0.1954 1.0000
4.500 0.5738 0.00827 0.00294 -0.0021 0.1913 1.0000
4.750 0.6042 0.00841 0.00306 -0.0029 0.1857 1.0000
5.000 0.6345 0.00861 0.00323 -0.0036 0.1797 1.0000
5.250 0.6646 0.00871 0.00335 -0.0043 0.1754 1.0000
5.500 0.6946 0.00888 0.00349 -0.0049 0.1700 1.0000
5.750 0.7245 0.00907 0.00366 -0.0056 0.1645 1.0000
6.000 0.7542 0.00920 0.00381 -0.0061 0.1590 1.0000
6.250 0.7838 0.00943 0.00399 -0.0068 0.1512 1.0000
6.500 0.8132 0.00958 0.00413 -0.0073 0.1437 1.0000
6.750 0.8425 0.00981 0.00434 -0.0079 0.1356 1.0000
7.000 0.8716 0.01004 0.00454 -0.0084 0.1268 1.0000
7.250 0.9006 0.01028 0.00476 -0.0089 0.1186 1.0000
7.500 0.9293 0.01058 0.00502 -0.0095 0.1082 1.0000
7.750 0.9576 0.01092 0.00531 -0.0100 0.0963 1.0000
8.000 0.9857 0.01131 0.00563 -0.0104 0.0847 1.0000
8.250 1.0134 0.01173 0.00600 -0.0109 0.0733 1.0000
8.500 1.0408 0.01218 0.00640 -0.0113 0.0625 1.0000
8.750 1.0679 0.01266 0.00683 -0.0116 0.0528 1.0000
9.000 1.0946 0.01317 0.00729 -0.0119 0.0434 1.0000
9.250 1.1208 0.01376 0.00782 -0.0122 0.0342 1.0000
9.500 1.1466 0.01437 0.00839 -0.0123 0.0273 1.0000
9.750 1.1724 0.01493 0.00897 -0.0125 0.0232 1.0000
10.000 1.1971 0.01568 0.00972 -0.0125 0.0195 1.0000
10.250 1.2228 0.01616 0.01026 -0.0126 0.0184 1.0000
10.500 1.2477 0.01673 0.01086 -0.0127 0.0170 1.0000
10.750 1.2711 0.01752 0.01168 -0.0126 0.0155 1.0000
11.000 1.2939 0.01834 0.01260 -0.0124 0.0145 1.0000
11.250 1.3175 0.01893 0.01326 -0.0123 0.0140 1.0000
11.500 1.3402 0.01961 0.01400 -0.0121 0.0133 1.0000
11.750 1.3620 0.02034 0.01479 -0.0119 0.0127 1.0000
12.000 1.3823 0.02120 0.01572 -0.0115 0.0121 1.0000
12.250 1.3989 0.02241 0.01701 -0.0108 0.0115 1.0000
12.500 1.4089 0.02416 0.01893 -0.0096 0.0110 1.0000
12.750 1.4255 0.02507 0.01992 -0.0090 0.0108 1.0000
13.000 1.4373 0.02608 0.02102 -0.0078 0.0106 1.0000
13.250 1.4480 0.02718 0.02222 -0.0065 0.0104 1.0000
13.500 1.4582 0.02838 0.02350 -0.0053 0.0101 1.0000
13.750 1.4676 0.02968 0.02489 -0.0042 0.0098 1.0000
14.000 1.4758 0.03113 0.02643 -0.0031 0.0095 1.0000
14.250 1.4831 0.03268 0.02805 -0.0021 0.0093 1.0000
14.500 1.4886 0.03444 0.02991 -0.0012 0.0091 1.0000
14.750 1.4910 0.03654 0.03211 -0.0004 0.0089 1.0000
15.000 1.4891 0.03915 0.03483 0.0003 0.0087 1.0000
15.250 1.4826 0.04239 0.03819 0.0007 0.0085 1.0000
15.500 1.4708 0.04643 0.04237 0.0007 0.0084 1.0000
15.750 1.4546 0.05143 0.04754 -0.0003 0.0083 1.0000
16.000 1.4358 0.05741 0.05369 -0.0024 0.0082 1.0000
16.250 1.4140 0.06498 0.06145 -0.0064 0.0082 1.0000
16.500 1.3923 0.07370 0.07035 -0.0117 0.0082 1.0000
16.750 1.3709 0.08271 0.07952 -0.0169 0.0082 1.0000
17.000 1.3458 0.09197 0.08893 -0.0217 0.0083 1.0000
17.250 1.3200 0.10097 0.09805 -0.0263 0.0083 1.0000
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Polar data table (+)
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