NASA/AMES A-01 AIRFOIL (ames01-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/AMES A-01 AIRFOIL (ames01-il) Reynolds number: 500,000 Max Cl/Cd: 74.59 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ames01-il-500000-n5.txt Download as CSV file: xf-ames01-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/AMES A-01 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -1.1853 0.05054 0.04758 -0.0243 1.0000 0.0077
-14.000 -1.2128 0.04468 0.04143 -0.0254 1.0000 0.0076
-13.750 -1.2293 0.04086 0.03737 -0.0238 1.0000 0.0077
-13.500 -1.2381 0.03809 0.03438 -0.0211 1.0000 0.0078
-13.250 -1.2358 0.03577 0.03188 -0.0194 1.0000 0.0080
-13.000 -1.2275 0.03381 0.02975 -0.0180 1.0000 0.0082
-12.750 -1.2155 0.03211 0.02789 -0.0169 1.0000 0.0085
-12.500 -1.2012 0.03053 0.02614 -0.0159 1.0000 0.0087
-12.250 -1.1850 0.02909 0.02453 -0.0151 1.0000 0.0091
-12.000 -1.1672 0.02773 0.02300 -0.0144 1.0000 0.0094
-11.750 -1.1482 0.02645 0.02154 -0.0138 1.0000 0.0098
-11.500 -1.1278 0.02526 0.02018 -0.0132 1.0000 0.0101
-11.250 -1.1056 0.02422 0.01900 -0.0130 0.9822 0.0104
-11.000 -1.0835 0.02340 0.01809 -0.0125 0.9709 0.0108
-10.750 -1.0624 0.02268 0.01725 -0.0116 0.9629 0.0111
-10.500 -1.0411 0.02199 0.01646 -0.0107 0.9571 0.0115
-10.250 -1.0193 0.02132 0.01567 -0.0099 0.9520 0.0119
-10.000 -0.9981 0.02065 0.01488 -0.0089 0.9472 0.0123
-9.750 -0.9754 0.01999 0.01410 -0.0082 0.9430 0.0128
-9.500 -0.9521 0.01935 0.01334 -0.0075 0.9389 0.0131
-9.250 -0.9290 0.01877 0.01266 -0.0068 0.9352 0.0135
-9.000 -0.9057 0.01829 0.01211 -0.0060 0.9318 0.0140
-8.750 -0.8803 0.01783 0.01160 -0.0057 0.9282 0.0146
-8.500 -0.8552 0.01738 0.01109 -0.0053 0.9247 0.0153
-8.250 -0.8303 0.01696 0.01058 -0.0048 0.9215 0.0160
-8.000 -0.8058 0.01654 0.01007 -0.0042 0.9184 0.0167
-7.750 -0.7801 0.01607 0.00954 -0.0039 0.9153 0.0174
-7.500 -0.7539 0.01567 0.00912 -0.0037 0.9121 0.0181
-7.250 -0.7279 0.01530 0.00870 -0.0033 0.9088 0.0188
-7.000 -0.7022 0.01495 0.00830 -0.0029 0.9058 0.0196
-6.500 -0.6496 0.01422 0.00743 -0.0023 0.8999 0.0211
-6.250 -0.6229 0.01383 0.00701 -0.0021 0.8966 0.0219
-6.000 -0.5961 0.01354 0.00672 -0.0019 0.8934 0.0231
-5.750 -0.5694 0.01329 0.00645 -0.0017 0.8905 0.0243
-5.500 -0.5428 0.01306 0.00617 -0.0014 0.8879 0.0258
-5.250 -0.5147 0.01282 0.00590 -0.0014 0.8845 0.0270
-5.000 -0.4875 0.01250 0.00560 -0.0013 0.8811 0.0290
-4.750 -0.4601 0.01230 0.00540 -0.0012 0.8776 0.0308
-4.500 -0.4333 0.01213 0.00519 -0.0008 0.8738 0.0328
-4.250 -0.4054 0.01191 0.00494 -0.0008 0.8683 0.0341
-4.000 -0.3789 0.01154 0.00456 -0.0004 0.8620 0.0364
-3.750 -0.3520 0.01130 0.00431 -0.0001 0.8560 0.0385
-3.500 -0.3241 0.01109 0.00409 0.0000 0.8485 0.0409
-3.250 -0.2971 0.01091 0.00385 0.0004 0.8424 0.0427
-3.000 -0.2690 0.01065 0.00358 0.0004 0.8344 0.0449
-2.750 -0.2419 0.01042 0.00333 0.0007 0.8268 0.0481
-2.500 -0.2137 0.01023 0.00314 0.0007 0.8170 0.0515
-2.250 -0.1857 0.01009 0.00295 0.0009 0.8073 0.0544
-2.000 -0.1580 0.00989 0.00274 0.0010 0.7965 0.0594
-1.750 -0.1299 0.00973 0.00257 0.0011 0.7829 0.0656
-1.500 -0.1019 0.00957 0.00240 0.0012 0.7672 0.0750
-1.250 -0.0738 0.00940 0.00224 0.0013 0.7502 0.0922
-1.000 -0.0464 0.00906 0.00207 0.0013 0.7293 0.1541
-0.750 -0.0206 0.00843 0.00189 0.0014 0.7049 0.3043
-0.500 0.0049 0.00785 0.00174 0.0016 0.6723 0.4625
-0.250 0.0299 0.00741 0.00166 0.0020 0.6263 0.6083
0.000 0.0539 0.00717 0.00166 0.0028 0.5606 0.7377
0.250 0.0773 0.00718 0.00174 0.0039 0.4840 0.8389
0.500 0.1034 0.00742 0.00188 0.0045 0.4110 0.9047
0.750 0.1369 0.00780 0.00204 0.0035 0.3498 0.9462
1.000 0.1730 0.00812 0.00218 0.0017 0.3119 0.9680
1.250 0.2102 0.00836 0.00228 -0.0003 0.2893 0.9779
1.500 0.2441 0.00855 0.00236 -0.0017 0.2740 0.9841
1.750 0.2810 0.00872 0.00243 -0.0037 0.2609 0.9867
2.000 0.3161 0.00888 0.00251 -0.0054 0.2500 0.9896
2.250 0.3503 0.00902 0.00259 -0.0068 0.2425 0.9928
2.500 0.3845 0.00917 0.00268 -0.0083 0.2355 0.9953
2.750 0.4193 0.00930 0.00277 -0.0099 0.2299 0.9974
3.000 0.4539 0.00944 0.00287 -0.0114 0.2241 0.9995
3.250 0.4818 0.00958 0.00296 -0.0116 0.2186 1.0000
3.500 0.5075 0.00969 0.00305 -0.0112 0.2147 1.0000
3.750 0.5333 0.00979 0.00314 -0.0108 0.2110 1.0000
4.000 0.5590 0.00992 0.00325 -0.0105 0.2070 1.0000
4.250 0.5846 0.01009 0.00338 -0.0101 0.2026 1.0000
4.500 0.6104 0.01021 0.00351 -0.0097 0.1991 1.0000
4.750 0.6362 0.01034 0.00365 -0.0094 0.1956 1.0000
5.000 0.6620 0.01050 0.00380 -0.0090 0.1914 1.0000
5.250 0.6876 0.01070 0.00396 -0.0087 0.1868 1.0000
5.500 0.7136 0.01082 0.00412 -0.0083 0.1831 1.0000
5.750 0.7395 0.01098 0.00429 -0.0080 0.1784 1.0000
6.000 0.7652 0.01119 0.00446 -0.0077 0.1734 1.0000
6.250 0.7911 0.01134 0.00464 -0.0074 0.1683 1.0000
6.500 0.8170 0.01153 0.00483 -0.0071 0.1625 1.0000
6.750 0.8427 0.01174 0.00504 -0.0068 0.1575 1.0000
7.000 0.8687 0.01193 0.00525 -0.0065 0.1511 1.0000
7.250 0.8944 0.01218 0.00546 -0.0063 0.1428 1.0000
7.500 0.9201 0.01243 0.00570 -0.0061 0.1337 1.0000
7.750 0.9457 0.01270 0.00597 -0.0058 0.1260 1.0000
8.000 0.9711 0.01302 0.00626 -0.0056 0.1166 1.0000
8.250 0.9961 0.01339 0.00660 -0.0053 0.1050 1.0000
8.500 1.0207 0.01381 0.00697 -0.0050 0.0922 1.0000
8.750 1.0448 0.01431 0.00740 -0.0047 0.0787 1.0000
9.000 1.0686 0.01484 0.00789 -0.0043 0.0671 1.0000
9.250 1.0921 0.01540 0.00842 -0.0040 0.0575 1.0000
9.500 1.1154 0.01597 0.00897 -0.0035 0.0493 1.0000
9.750 1.1387 0.01651 0.00952 -0.0031 0.0428 1.0000
10.000 1.1614 0.01711 0.01012 -0.0026 0.0372 1.0000
10.250 1.1837 0.01773 0.01074 -0.0021 0.0323 1.0000
10.500 1.2059 0.01832 0.01138 -0.0016 0.0290 1.0000
10.750 1.2276 0.01895 0.01203 -0.0010 0.0261 1.0000
11.000 1.2483 0.01966 0.01278 -0.0003 0.0236 1.0000
11.250 1.2694 0.02027 0.01346 0.0003 0.0220 1.0000
11.500 1.2893 0.02096 0.01420 0.0011 0.0205 1.0000
11.750 1.3077 0.02177 0.01507 0.0020 0.0191 1.0000
12.000 1.3252 0.02262 0.01599 0.0030 0.0181 1.0000
12.250 1.3428 0.02336 0.01683 0.0040 0.0174 1.0000
12.500 1.3589 0.02418 0.01774 0.0052 0.0167 1.0000
12.750 1.3729 0.02507 0.01872 0.0065 0.0161 1.0000
13.000 1.3828 0.02604 0.01977 0.0085 0.0155 1.0000
13.250 1.3906 0.02717 0.02100 0.0104 0.0150 1.0000
13.500 1.3969 0.02851 0.02242 0.0122 0.0145 1.0000
13.750 1.4000 0.03018 0.02420 0.0139 0.0140 1.0000
14.000 1.4047 0.03181 0.02593 0.0153 0.0137 1.0000
14.250 1.4101 0.03346 0.02771 0.0163 0.0134 1.0000
14.500 1.4138 0.03536 0.02972 0.0172 0.0132 1.0000
14.750 1.4158 0.03754 0.03203 0.0178 0.0128 1.0000
15.000 1.4159 0.04005 0.03466 0.0181 0.0125 1.0000
15.250 1.4137 0.04303 0.03778 0.0179 0.0123 1.0000
15.500 1.4083 0.04664 0.04153 0.0171 0.0121 1.0000
15.750 1.4007 0.05094 0.04597 0.0155 0.0119 1.0000
16.000 1.3876 0.05649 0.05169 0.0128 0.0118 1.0000
16.250 1.3688 0.06363 0.05902 0.0089 0.0117 1.0000
16.500 1.3436 0.07235 0.06794 0.0040 0.0117 1.0000
16.750 1.3136 0.08183 0.07760 -0.0010 0.0118 1.0000
17.000 1.2823 0.09115 0.08706 -0.0055 0.0119 1.0000
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