NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.4 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ames03-il-1000000-n5.txt Download as CSV file: xf-ames03-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -1.2558 0.05278 0.05043 0.0035 0.8554 0.0056
-13.500 -1.3030 0.04239 0.03957 0.0027 0.8496 0.0056
-13.250 -1.3142 0.03954 0.03652 0.0055 0.8465 0.0057
-13.000 -1.3134 0.03693 0.03370 0.0072 0.8439 0.0058
-12.750 -1.3068 0.03468 0.03124 0.0086 0.8415 0.0058
-12.500 -1.2967 0.03264 0.02898 0.0098 0.8393 0.0059
-12.250 -1.2833 0.03088 0.02702 0.0109 0.8372 0.0060
-12.000 -1.2673 0.02930 0.02526 0.0118 0.8350 0.0061
-11.750 -1.2497 0.02784 0.02364 0.0125 0.8326 0.0062
-11.500 -1.2306 0.02654 0.02217 0.0132 0.8303 0.0062
-11.250 -1.2098 0.02544 0.02092 0.0137 0.8282 0.0063
-11.000 -1.1877 0.02451 0.01986 0.0142 0.8262 0.0064
-10.750 -1.1677 0.02305 0.01822 0.0148 0.8243 0.0066
-10.250 -1.1218 0.02107 0.01600 0.0156 0.8207 0.0070
-10.000 -1.0972 0.02034 0.01519 0.0158 0.8186 0.0071
-9.750 -1.0722 0.01965 0.01441 0.0159 0.8164 0.0073
-9.500 -1.0468 0.01897 0.01364 0.0161 0.8144 0.0074
-9.250 -1.0212 0.01833 0.01291 0.0163 0.8125 0.0076
-9.000 -0.9954 0.01769 0.01218 0.0164 0.8107 0.0078
-8.750 -0.9692 0.01709 0.01149 0.0165 0.8090 0.0080
-8.500 -0.9429 0.01651 0.01081 0.0166 0.8074 0.0082
-8.250 -0.9160 0.01597 0.01019 0.0166 0.8057 0.0084
-8.000 -0.8890 0.01544 0.00960 0.0166 0.8039 0.0086
-7.750 -0.8616 0.01499 0.00907 0.0166 0.8019 0.0088
-7.500 -0.8343 0.01449 0.00851 0.0165 0.8000 0.0091
-7.250 -0.8071 0.01391 0.00788 0.0165 0.7982 0.0096
-7.000 -0.7794 0.01352 0.00745 0.0164 0.7966 0.0100
-6.750 -0.7515 0.01315 0.00703 0.0163 0.7950 0.0103
-6.500 -0.7234 0.01280 0.00663 0.0162 0.7935 0.0107
-6.250 -0.6952 0.01246 0.00625 0.0161 0.7920 0.0111
-6.000 -0.6667 0.01212 0.00588 0.0159 0.7905 0.0115
-5.750 -0.6381 0.01183 0.00555 0.0157 0.7888 0.0119
-5.500 -0.6095 0.01148 0.00517 0.0155 0.7871 0.0124
-5.250 -0.5808 0.01115 0.00483 0.0153 0.7853 0.0131
-5.000 -0.5520 0.01089 0.00455 0.0151 0.7835 0.0139
-4.750 -0.5232 0.01066 0.00430 0.0149 0.7812 0.0148
-4.500 -0.4943 0.01045 0.00405 0.0147 0.7784 0.0156
-4.250 -0.4652 0.01019 0.00379 0.0144 0.7757 0.0170
-4.000 -0.4360 0.00996 0.00357 0.0141 0.7727 0.0185
-3.750 -0.4067 0.00977 0.00337 0.0138 0.7694 0.0200
-3.500 -0.3774 0.00958 0.00316 0.0136 0.7670 0.0216
-3.250 -0.3482 0.00939 0.00298 0.0133 0.7643 0.0248
-3.000 -0.3188 0.00922 0.00281 0.0130 0.7610 0.0275
-2.750 -0.2892 0.00903 0.00265 0.0126 0.7571 0.0324
-2.500 -0.2597 0.00886 0.00250 0.0123 0.7535 0.0387
-2.250 -0.2302 0.00869 0.00236 0.0119 0.7503 0.0487
-2.000 -0.2007 0.00851 0.00223 0.0116 0.7468 0.0634
-1.750 -0.1709 0.00832 0.00212 0.0112 0.7418 0.0829
-1.500 -0.1413 0.00806 0.00199 0.0107 0.7355 0.1216
-1.250 -0.1115 0.00778 0.00188 0.0102 0.7290 0.1719
-1.000 -0.0817 0.00748 0.00175 0.0096 0.7183 0.2341
-0.750 -0.0516 0.00710 0.00163 0.0089 0.7025 0.3231
-0.500 -0.0213 0.00643 0.00149 0.0079 0.6791 0.4936
-0.250 0.0096 0.00613 0.00140 0.0070 0.6416 0.5979
0.000 0.0479 0.00673 0.00155 0.0037 0.4246 0.6951
0.250 0.0803 0.00696 0.00165 0.0023 0.3356 0.7527
0.500 0.1112 0.00711 0.00172 0.0015 0.2905 0.7862
0.750 0.1407 0.00717 0.00180 0.0011 0.2660 0.8249
1.000 0.1701 0.00725 0.00187 0.0007 0.2497 0.8502
1.250 0.1998 0.00733 0.00192 0.0003 0.2372 0.8617
1.500 0.2296 0.00743 0.00197 -0.0001 0.2274 0.8697
1.750 0.2591 0.00750 0.00203 -0.0005 0.2213 0.8776
2.000 0.2887 0.00758 0.00209 -0.0009 0.2153 0.8847
2.250 0.3181 0.00767 0.00216 -0.0012 0.2095 0.8920
2.500 0.3476 0.00775 0.00223 -0.0016 0.2048 0.8987
2.750 0.3767 0.00783 0.00230 -0.0019 0.1995 0.9055
3.000 0.4062 0.00794 0.00238 -0.0023 0.1945 0.9122
3.250 0.4348 0.00800 0.00246 -0.0025 0.1908 0.9186
3.500 0.4638 0.00810 0.00255 -0.0027 0.1860 0.9253
3.750 0.4924 0.00822 0.00265 -0.0030 0.1803 0.9316
4.000 0.5208 0.00830 0.00274 -0.0031 0.1768 0.9385
4.250 0.5492 0.00839 0.00284 -0.0033 0.1718 0.9451
4.500 0.5772 0.00852 0.00294 -0.0034 0.1657 0.9524
4.750 0.6053 0.00861 0.00304 -0.0035 0.1611 0.9597
5.000 0.6333 0.00872 0.00315 -0.0036 0.1558 0.9683
5.250 0.6624 0.00885 0.00327 -0.0040 0.1499 0.9772
5.500 0.6931 0.00898 0.00339 -0.0048 0.1446 0.9875
5.750 0.7241 0.00915 0.00354 -0.0057 0.1382 1.0000
6.000 0.7538 0.00933 0.00372 -0.0063 0.1322 1.0000
6.250 0.7833 0.00957 0.00391 -0.0069 0.1234 1.0000
6.500 0.8126 0.00985 0.00412 -0.0076 0.1109 1.0000
6.750 0.8417 0.01014 0.00436 -0.0081 0.0997 1.0000
7.000 0.8705 0.01045 0.00462 -0.0087 0.0886 1.0000
7.250 0.8991 0.01078 0.00490 -0.0092 0.0789 1.0000
7.500 0.9275 0.01114 0.00521 -0.0097 0.0690 1.0000
7.750 0.9556 0.01153 0.00556 -0.0102 0.0592 1.0000
8.000 0.9833 0.01195 0.00593 -0.0106 0.0506 1.0000
8.250 1.0110 0.01234 0.00629 -0.0110 0.0435 1.0000
8.500 1.0383 0.01279 0.00670 -0.0114 0.0359 1.0000
8.750 1.0652 0.01326 0.00714 -0.0117 0.0293 1.0000
9.000 1.0920 0.01374 0.00759 -0.0119 0.0244 1.0000
9.250 1.1185 0.01421 0.00806 -0.0122 0.0209 1.0000
9.500 1.1449 0.01467 0.00852 -0.0124 0.0183 1.0000
9.750 1.1709 0.01516 0.00903 -0.0126 0.0161 1.0000
10.000 1.1967 0.01566 0.00955 -0.0127 0.0144 1.0000
10.250 1.2224 0.01612 0.01005 -0.0128 0.0135 1.0000
10.500 1.2475 0.01665 0.01061 -0.0129 0.0125 1.0000
10.750 1.2720 0.01723 0.01122 -0.0129 0.0116 1.0000
11.000 1.2962 0.01782 0.01186 -0.0128 0.0109 1.0000
11.250 1.3203 0.01836 0.01246 -0.0128 0.0105 1.0000
11.500 1.3438 0.01894 0.01310 -0.0127 0.0100 1.0000
11.750 1.3666 0.01957 0.01378 -0.0125 0.0095 1.0000
12.000 1.3886 0.02025 0.01451 -0.0123 0.0091 1.0000
12.250 1.4096 0.02101 0.01533 -0.0120 0.0087 1.0000
12.500 1.4290 0.02188 0.01627 -0.0115 0.0082 1.0000
12.750 1.4475 0.02277 0.01724 -0.0109 0.0080 1.0000
13.000 1.4660 0.02359 0.01814 -0.0105 0.0078 1.0000
13.250 1.4825 0.02450 0.01914 -0.0099 0.0076 1.0000
13.500 1.4949 0.02548 0.02020 -0.0087 0.0075 1.0000
13.750 1.5058 0.02654 0.02135 -0.0074 0.0073 1.0000
14.000 1.5168 0.02765 0.02254 -0.0062 0.0071 1.0000
14.250 1.5272 0.02885 0.02382 -0.0051 0.0068 1.0000
14.500 1.5363 0.03017 0.02522 -0.0040 0.0066 1.0000
14.750 1.5440 0.03165 0.02677 -0.0030 0.0064 1.0000
15.000 1.5496 0.03336 0.02857 -0.0020 0.0062 1.0000
15.250 1.5524 0.03537 0.03067 -0.0010 0.0060 1.0000
15.500 1.5518 0.03778 0.03320 -0.0002 0.0058 1.0000
15.750 1.5493 0.04047 0.03602 0.0004 0.0057 1.0000
16.000 1.5487 0.04311 0.03877 0.0007 0.0056 1.0000
16.250 1.5461 0.04608 0.04186 0.0007 0.0056 1.0000
16.500 1.5401 0.04966 0.04557 0.0003 0.0055 1.0000
16.750 1.5294 0.05414 0.05019 -0.0009 0.0055 1.0000
17.000 1.5143 0.05982 0.05604 -0.0032 0.0054 1.0000
17.250 1.4876 0.06860 0.06502 -0.0081 0.0055 1.0000
17.500 1.4338 0.08432 0.08105 -0.0176 0.0056 1.0000
17.750 1.3510 0.10428 0.10128 -0.0279 0.0057 1.0000
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