AH 88-K-130/20 (ah88k130-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 88-K-130/20 (ah88k130-il) Reynolds number: 500,000 Max Cl/Cd: 113.68 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah88k130-il-500000-n5.txt Download as CSV file: xf-ah88k130-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 88-K-130/20
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1304 0.08424 0.08084 -0.1154 0.8184 0.0070
-10.000 -0.1301 0.08022 0.07685 -0.1173 0.8173 0.0070
-9.750 -0.1301 0.07625 0.07290 -0.1192 0.8163 0.0067
-9.500 -0.1330 0.07173 0.06843 -0.1215 0.8150 0.0068
-9.250 -0.1360 0.06732 0.06405 -0.1240 0.8137 0.0069
-9.000 -0.1448 0.06182 0.05860 -0.1279 0.8120 0.0066
-8.750 -0.1590 0.05628 0.05305 -0.1323 0.8100 0.0067
-8.500 -0.1783 0.05229 0.04901 -0.1325 0.8082 0.0065
-8.250 -0.1900 0.04798 0.04457 -0.1324 0.8067 0.0065
-8.000 -0.1936 0.04410 0.04053 -0.1318 0.8052 0.0067
-7.750 -0.1967 0.03963 0.03587 -0.1306 0.8035 0.0066
-7.500 -0.1946 0.03539 0.03138 -0.1292 0.8015 0.0066
-7.250 -0.1898 0.03094 0.02660 -0.1275 0.7995 0.0067
-7.000 -0.1790 0.02719 0.02249 -0.1259 0.7978 0.0072
-6.750 -0.1657 0.02356 0.01843 -0.1244 0.7964 0.0075
-6.500 -0.1485 0.02062 0.01506 -0.1232 0.7951 0.0075
-6.250 -0.1277 0.01839 0.01244 -0.1224 0.7940 0.0074
-6.000 -0.1046 0.01677 0.01053 -0.1218 0.7928 0.0075
-5.750 -0.0803 0.01554 0.00908 -0.1214 0.7916 0.0076
-5.500 -0.0564 0.01457 0.00797 -0.1210 0.7900 0.0077
-5.250 -0.0322 0.01378 0.00705 -0.1206 0.7882 0.0080
-5.000 -0.0074 0.01315 0.00633 -0.1203 0.7865 0.0082
-4.750 0.0173 0.01250 0.00560 -0.1200 0.7849 0.0086
-4.500 0.0430 0.01205 0.00512 -0.1200 0.7833 0.0095
-4.250 0.0696 0.01174 0.00476 -0.1200 0.7819 0.0104
-4.000 0.0965 0.01144 0.00440 -0.1201 0.7805 0.0116
-3.750 0.1236 0.01115 0.00408 -0.1203 0.7792 0.0138
-3.500 0.1513 0.01099 0.00389 -0.1206 0.7780 0.0178
-3.250 0.1780 0.01073 0.00363 -0.1206 0.7764 0.0229
-3.000 0.2051 0.01057 0.00343 -0.1208 0.7746 0.0266
-2.750 0.2324 0.01041 0.00326 -0.1209 0.7728 0.0322
-2.500 0.2597 0.01020 0.00312 -0.1212 0.7711 0.0490
-2.250 0.2871 0.00993 0.00298 -0.1215 0.7693 0.0919
-2.000 0.3143 0.00953 0.00283 -0.1219 0.7675 0.1790
-1.750 0.3418 0.00904 0.00269 -0.1226 0.7659 0.3008
-1.500 0.3694 0.00822 0.00255 -0.1235 0.7644 0.5255
-1.250 0.3969 0.00785 0.00256 -0.1239 0.7627 0.6441
-1.000 0.4203 0.00779 0.00292 -0.1228 0.7604 0.7610
-0.750 0.4477 0.00795 0.00307 -0.1227 0.7581 0.7955
-0.500 0.4751 0.00803 0.00314 -0.1227 0.7558 0.8064
-0.250 0.5028 0.00806 0.00315 -0.1228 0.7536 0.8126
0.000 0.5309 0.00809 0.00316 -0.1230 0.7516 0.8184
0.250 0.5597 0.00813 0.00316 -0.1233 0.7499 0.8243
0.500 0.5860 0.00817 0.00323 -0.1231 0.7471 0.8282
0.750 0.6134 0.00820 0.00328 -0.1233 0.7441 0.8316
1.000 0.6417 0.00821 0.00328 -0.1236 0.7413 0.8345
1.250 0.6707 0.00821 0.00326 -0.1241 0.7387 0.8371
1.500 0.6989 0.00820 0.00324 -0.1244 0.7363 0.8388
1.750 0.7251 0.00820 0.00330 -0.1243 0.7308 0.8408
2.000 0.7523 0.00814 0.00325 -0.1243 0.7245 0.8430
2.250 0.7792 0.00810 0.00324 -0.1243 0.7162 0.8452
2.500 0.8069 0.00807 0.00320 -0.1245 0.7099 0.8473
2.750 0.8343 0.00808 0.00324 -0.1246 0.7024 0.8493
3.000 0.8617 0.00808 0.00323 -0.1247 0.6942 0.8513
3.250 0.8874 0.00809 0.00324 -0.1245 0.6837 0.8531
3.500 0.9125 0.00814 0.00327 -0.1241 0.6705 0.8551
3.750 0.9367 0.00824 0.00334 -0.1235 0.6540 0.8572
4.000 0.9588 0.00844 0.00344 -0.1225 0.6297 0.8593
4.250 0.9795 0.00871 0.00360 -0.1213 0.6019 0.8613
4.500 1.0006 0.00899 0.00381 -0.1203 0.5781 0.8637
4.750 1.0189 0.00932 0.00407 -0.1186 0.5500 0.8660
5.000 1.0280 0.00992 0.00445 -0.1152 0.4960 0.8687
5.250 1.0246 0.01093 0.00506 -0.1096 0.4191 0.8715
5.500 1.0177 0.01195 0.00575 -0.1035 0.3522 0.8746
5.750 1.0144 0.01309 0.00657 -0.0984 0.2880 0.8782
6.000 1.0140 0.01417 0.00739 -0.0941 0.2313 0.8813
6.250 1.0163 0.01529 0.00825 -0.0905 0.1788 0.8838
6.500 1.0218 0.01636 0.00911 -0.0875 0.1327 0.8860
6.750 1.0315 0.01728 0.00992 -0.0853 0.1004 0.8884
7.000 1.0432 0.01815 0.01069 -0.0834 0.0753 0.8907
7.250 1.0534 0.01912 0.01154 -0.0814 0.0507 0.8925
7.500 1.0662 0.01992 0.01230 -0.0797 0.0365 0.8944
7.750 1.0800 0.02069 0.01307 -0.0782 0.0300 0.8963
8.000 1.0966 0.02131 0.01376 -0.0771 0.0259 0.8984
8.250 1.1104 0.02214 0.01461 -0.0757 0.0175 0.9007
8.500 1.1232 0.02306 0.01551 -0.0742 0.0129 0.9030
8.750 1.1375 0.02386 0.01639 -0.0728 0.0114 0.9055
9.000 1.1501 0.02474 0.01734 -0.0713 0.0100 0.9088
9.250 1.1611 0.02577 0.01845 -0.0695 0.0089 0.9124
9.500 1.1721 0.02683 0.01962 -0.0678 0.0082 0.9164
9.750 1.1842 0.02776 0.02064 -0.0663 0.0077 0.9218
10.000 1.1964 0.02868 0.02165 -0.0648 0.0070 0.9298
10.250 1.2073 0.02967 0.02276 -0.0632 0.0063 0.9447
10.500 1.2180 0.03078 0.02396 -0.0619 0.0058 1.0000
10.750 1.2264 0.03233 0.02559 -0.0605 0.0053 1.0000
11.000 1.2352 0.03386 0.02721 -0.0591 0.0051 1.0000
11.250 1.2462 0.03524 0.02867 -0.0580 0.0049 1.0000
11.500 1.2559 0.03675 0.03029 -0.0569 0.0047 1.0000
11.750 1.2661 0.03825 0.03188 -0.0558 0.0043 1.0000
12.000 1.2744 0.03996 0.03369 -0.0547 0.0042 1.0000
12.250 1.2830 0.04168 0.03550 -0.0536 0.0039 1.0000
12.500 1.2919 0.04339 0.03731 -0.0527 0.0037 1.0000
12.750 1.2996 0.04527 0.03929 -0.0518 0.0036 1.0000
13.000 1.3077 0.04714 0.04127 -0.0510 0.0035 1.0000
13.250 1.3138 0.04928 0.04351 -0.0501 0.0034 1.0000
13.500 1.3187 0.05160 0.04595 -0.0493 0.0032 1.0000
13.750 1.3219 0.05420 0.04868 -0.0484 0.0032 1.0000
14.000 1.3199 0.05755 0.05221 -0.0474 0.0030 1.0000
14.250 1.3229 0.06035 0.05517 -0.0468 0.0030 1.0000
14.500 1.3253 0.06327 0.05827 -0.0464 0.0030 1.0000
14.750 1.3268 0.06636 0.06153 -0.0461 0.0029 1.0000
15.000 1.3267 0.06972 0.06508 -0.0459 0.0029 1.0000
15.250 1.3256 0.07332 0.06887 -0.0460 0.0028 1.0000
15.500 1.3217 0.07744 0.07318 -0.0462 0.0027 1.0000
15.750 1.3173 0.08171 0.07765 -0.0468 0.0027 1.0000
16.000 1.3112 0.08635 0.08248 -0.0477 0.0026 1.0000
16.250 1.3035 0.09141 0.08774 -0.0489 0.0025 1.0000
16.500 1.2936 0.09701 0.09354 -0.0506 0.0025 1.0000
16.750 1.2820 0.10315 0.09989 -0.0527 0.0025 1.0000
17.000 1.2694 0.10968 0.10661 -0.0554 0.0024 1.0000
17.250 1.2549 0.11688 0.11402 -0.0588 0.0024 1.0000
17.500 1.2393 0.12467 0.12199 -0.0628 0.0024 1.0000
17.750 1.2226 0.13315 0.13066 -0.0677 0.0024 1.0000
18.000 1.2043 0.14248 0.14018 -0.0733 0.0024 1.0000
18.250 1.1854 0.15253 0.15041 -0.0797 0.0025 1.0000
18.500 1.1634 0.16425 0.16231 -0.0872 0.0025 1.0000
18.750 1.1366 0.17855 0.17677 -0.0960 0.0026 1.0000
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Polar data table (+)
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