TRAINER60 (trainer60-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: TRAINER60 (trainer60-il) Reynolds number: 100,000 Max Cl/Cd: 36.69 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-trainer60-il-100000.txt Download as CSV file: xf-trainer60-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: TRAINER60
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.4561 0.18031 0.17515 0.0234 1.0000 0.1418
-17.250 -0.4507 0.17811 0.17293 0.0224 1.0000 0.1466
-17.000 -1.1463 0.09755 0.09080 -0.0116 1.0000 0.0857
-16.500 -1.1051 0.09646 0.08994 -0.0097 1.0000 0.0907
-16.250 -1.1424 0.08729 0.08046 -0.0144 1.0000 0.0911
-16.000 -0.9026 0.09317 0.08718 -0.0214 1.0000 0.1034
-15.750 -0.9636 0.08188 0.07555 -0.0259 1.0000 0.1031
-15.500 -1.2066 0.06918 0.06151 -0.0215 1.0000 0.0948
-15.250 -1.1774 0.06933 0.06197 -0.0202 1.0000 0.0987
-15.000 -1.1832 0.06548 0.05797 -0.0211 1.0000 0.1013
-14.750 -1.1964 0.06091 0.05310 -0.0223 1.0000 0.1037
-14.500 -1.1802 0.05965 0.05205 -0.0217 1.0000 0.1078
-14.250 -1.1823 0.05651 0.04881 -0.0222 1.0000 0.1118
-14.000 -1.1838 0.05347 0.04569 -0.0225 1.0000 0.1162
-13.750 -1.1801 0.05121 0.04350 -0.0225 1.0000 0.1215
-13.500 -1.1842 0.04816 0.04031 -0.0226 1.0000 0.1271
-13.250 -1.1816 0.04607 0.03830 -0.0223 1.0000 0.1336
-13.000 -1.1845 0.04361 0.03580 -0.0218 1.0000 0.1409
-12.750 -1.1906 0.04128 0.03337 -0.0208 1.0000 0.1492
-12.500 -1.1888 0.03973 0.03192 -0.0195 1.0000 0.1580
-12.250 -1.1956 0.03789 0.02998 -0.0170 1.0000 0.1675
-12.000 -1.1989 0.03670 0.02876 -0.0139 1.0000 0.1774
-11.750 -1.1917 0.03574 0.02789 -0.0119 1.0000 0.1881
-11.500 -1.1886 0.03455 0.02657 -0.0094 1.0000 0.1987
-11.250 -1.1770 0.03385 0.02587 -0.0076 1.0000 0.2095
-11.000 -1.1606 0.03310 0.02519 -0.0063 1.0000 0.2195
-10.750 -1.1517 0.03224 0.02411 -0.0042 1.0000 0.2293
-10.500 -1.1275 0.03173 0.02380 -0.0037 1.0000 0.2386
-10.250 -1.1166 0.03088 0.02269 -0.0018 1.0000 0.2478
-10.000 -1.0900 0.03047 0.02251 -0.0016 1.0000 0.2565
-9.750 -1.0757 0.02971 0.02155 0.0001 1.0000 0.2654
-9.500 -1.0499 0.02927 0.02128 0.0004 1.0000 0.2737
-9.250 -1.0321 0.02870 0.02059 0.0017 1.0000 0.2828
-9.000 -1.0083 0.02827 0.02027 0.0023 1.0000 0.2914
-8.750 -0.9888 0.02789 0.01984 0.0035 1.0000 0.3012
-8.500 -0.9656 0.02749 0.01952 0.0043 1.0000 0.3101
-8.250 -0.9445 0.02711 0.01915 0.0053 1.0000 0.3192
-8.000 -0.9252 0.02635 0.01833 0.0064 1.0000 0.3269
-7.750 -0.9008 0.02595 0.01804 0.0070 1.0000 0.3340
-7.500 -0.8852 0.02524 0.01716 0.0087 1.0000 0.3422
-7.250 -0.8642 0.02470 0.01675 0.0097 1.0000 0.3492
-7.000 -0.8486 0.02433 0.01643 0.0114 1.0000 0.3569
-6.750 -0.8460 0.02386 0.01580 0.0148 1.0000 0.3649
-6.500 -0.8358 0.02370 0.01583 0.0170 1.0000 0.3712
-6.250 -0.7920 0.02303 0.01502 0.0130 0.9839 0.3858
-6.000 -0.7378 0.02265 0.01481 0.0080 0.9745 0.3999
-5.750 -0.6818 0.02219 0.01441 0.0025 0.9669 0.4161
-5.500 -0.6250 0.02185 0.01408 -0.0031 0.9586 0.4341
-5.250 -0.5721 0.02166 0.01387 -0.0080 0.9469 0.4523
-5.000 -0.5240 0.02169 0.01386 -0.0118 0.9332 0.4692
-4.750 -0.4861 0.02206 0.01435 -0.0132 0.9155 0.4809
-4.500 -0.4581 0.02223 0.01445 -0.0131 0.8981 0.4948
-4.250 -0.4323 0.02256 0.01484 -0.0121 0.8806 0.5054
-4.000 -0.4108 0.02255 0.01476 -0.0106 0.8644 0.5171
-3.750 -0.3843 0.02269 0.01495 -0.0095 0.8503 0.5270
-3.500 -0.3642 0.02255 0.01471 -0.0078 0.8350 0.5387
-3.250 -0.3379 0.02264 0.01487 -0.0067 0.8213 0.5477
-3.000 -0.3168 0.02244 0.01450 -0.0051 0.8098 0.5600
-2.750 -0.2896 0.02243 0.01459 -0.0042 0.7961 0.5680
-2.500 -0.2673 0.02232 0.01438 -0.0028 0.7836 0.5794
-2.250 -0.2413 0.02217 0.01422 -0.0017 0.7719 0.5883
-2.000 -0.2169 0.02218 0.01423 -0.0007 0.7593 0.5982
-1.750 -0.1930 0.02199 0.01395 0.0005 0.7487 0.6089
-1.500 -0.1671 0.02207 0.01410 0.0014 0.7361 0.6181
-1.250 -0.1444 0.02195 0.01384 0.0028 0.7256 0.6305
-1.000 -0.1177 0.02210 0.01411 0.0036 0.7135 0.6401
-0.750 -0.0952 0.02207 0.01398 0.0049 0.7035 0.6537
-0.500 -0.0677 0.02221 0.01422 0.0056 0.6934 0.6627
-0.250 -0.0444 0.02219 0.01416 0.0067 0.6825 0.6742
0.000 -0.0172 0.02217 0.01411 0.0074 0.6743 0.6830
0.250 0.0065 0.02230 0.01433 0.0082 0.6628 0.6930
0.500 0.0317 0.02223 0.01420 0.0091 0.6545 0.7039
0.750 0.0568 0.02237 0.01441 0.0099 0.6437 0.7133
1.000 0.0807 0.02222 0.01418 0.0110 0.6328 0.7251
1.250 0.1072 0.02225 0.01427 0.0119 0.6216 0.7343
1.500 0.1302 0.02216 0.01413 0.0131 0.6105 0.7474
1.750 0.1584 0.02217 0.01416 0.0139 0.6018 0.7565
2.000 0.1805 0.02222 0.01426 0.0149 0.5906 0.7692
2.250 0.2093 0.02216 0.01418 0.0156 0.5826 0.7788
2.500 0.2309 0.02230 0.01439 0.0167 0.5720 0.7924
2.750 0.2585 0.02226 0.01438 0.0176 0.5626 0.8024
3.000 0.2827 0.02231 0.01443 0.0186 0.5534 0.8154
3.250 0.3079 0.02234 0.01454 0.0196 0.5426 0.8268
3.500 0.3354 0.02225 0.01436 0.0204 0.5343 0.8395
3.750 0.3569 0.02235 0.01459 0.0218 0.5221 0.8540
4.000 0.3850 0.02217 0.01427 0.0225 0.5135 0.8691
4.250 0.4072 0.02222 0.01446 0.0236 0.5001 0.8852
4.500 0.4384 0.02191 0.01401 0.0236 0.4902 0.9026
4.750 0.4657 0.02169 0.01391 0.0236 0.4757 0.9242
5.000 0.5127 0.02143 0.01367 0.0197 0.4599 0.9437
5.250 0.5779 0.02144 0.01365 0.0123 0.4408 0.9557
5.500 0.6446 0.02173 0.01389 0.0047 0.4209 0.9627
5.750 0.7062 0.02211 0.01418 -0.0018 0.4023 0.9693
6.000 0.7620 0.02255 0.01457 -0.0073 0.3844 0.9786
6.250 0.8000 0.02324 0.01536 -0.0105 0.3698 1.0000
6.500 0.8110 0.02335 0.01526 -0.0084 0.3627 1.0000
6.750 0.8236 0.02390 0.01593 -0.0066 0.3526 1.0000
7.000 0.8460 0.02424 0.01613 -0.0059 0.3443 1.0000
7.250 0.8665 0.02497 0.01692 -0.0052 0.3360 1.0000
7.500 0.8892 0.02555 0.01751 -0.0046 0.3278 1.0000
7.750 0.9162 0.02609 0.01787 -0.0045 0.3211 1.0000
8.000 0.9353 0.02692 0.01893 -0.0036 0.3124 1.0000
8.250 0.9629 0.02711 0.01892 -0.0034 0.3039 1.0000
8.500 0.9824 0.02771 0.01965 -0.0026 0.2933 1.0000
8.750 1.0105 0.02777 0.01942 -0.0025 0.2833 1.0000
9.000 1.0285 0.02841 0.02028 -0.0015 0.2731 1.0000
9.250 1.0564 0.02879 0.02042 -0.0015 0.2651 1.0000
9.500 1.0737 0.02967 0.02157 -0.0005 0.2565 1.0000
9.750 1.0997 0.03008 0.02180 -0.0004 0.2482 1.0000
10.000 1.1169 0.03104 0.02295 0.0006 0.2395 1.0000
10.250 1.1413 0.03151 0.02329 0.0009 0.2305 1.0000
10.500 1.1563 0.03255 0.02452 0.0020 0.2213 1.0000
10.750 1.1811 0.03311 0.02482 0.0022 0.2113 1.0000
11.000 1.1895 0.03421 0.02622 0.0039 0.2009 1.0000
11.250 1.2033 0.03519 0.02719 0.0051 0.1898 1.0000
11.500 1.2173 0.03608 0.02791 0.0062 0.1778 1.0000
11.750 1.2179 0.03753 0.02952 0.0083 0.1658 1.0000
12.000 1.2137 0.03929 0.03137 0.0109 0.1554 1.0000
12.250 1.2139 0.04102 0.03305 0.0124 0.1462 1.0000
12.500 1.2141 0.04295 0.03495 0.0134 0.1377 1.0000
12.750 1.2110 0.04560 0.03774 0.0140 0.1303 1.0000
13.000 1.2204 0.04724 0.03918 0.0143 0.1241 1.0000
13.250 1.2146 0.05055 0.04274 0.0142 0.1189 1.0000
13.500 1.2228 0.05249 0.04458 0.0142 0.1142 1.0000
13.750 1.2229 0.05554 0.04775 0.0140 0.1104 1.0000
14.000 1.2228 0.05864 0.05099 0.0135 0.1070 1.0000
14.250 1.2379 0.06009 0.05229 0.0139 0.1036 1.0000
14.500 1.2362 0.06357 0.05592 0.0134 0.1011 1.0000
14.750 1.2269 0.06791 0.06051 0.0122 0.0991 1.0000
15.000 1.2221 0.07182 0.06456 0.0112 0.0971 1.0000
15.250 1.2364 0.07338 0.06601 0.0114 0.0945 1.0000
15.500 1.2416 0.07628 0.06894 0.0111 0.0927 1.0000
15.750 1.2148 0.08312 0.07611 0.0082 0.0919 1.0000
16.000 1.1808 0.09142 0.08475 0.0043 0.0915 1.0000
16.250 1.1282 0.10343 0.09713 -0.0022 0.0918 1.0000
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Polar data table (+)
Polar graphs
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