AH 88-K-130/20 (ah88k130-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 88-K-130/20 (ah88k130-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.16 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah88k130-il-1000000.txt Download as CSV file: xf-ah88k130-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1307 0.08785 0.08523 -0.1173 0.8250 0.0088
-10.500 -0.1273 0.08423 0.08161 -0.1192 0.8241 0.0088
-10.250 -0.1236 0.08083 0.07823 -0.1209 0.8232 0.0088
-10.000 -0.1191 0.07787 0.07527 -0.1224 0.8222 0.0090
-9.750 -0.1175 0.07410 0.07150 -0.1245 0.8211 0.0090
-9.500 -0.1129 0.07134 0.06875 -0.1260 0.8197 0.0093
-9.250 -0.1119 0.06780 0.06523 -0.1281 0.8187 0.0095
-9.000 -0.1153 0.06343 0.06090 -0.1309 0.8178 0.0095
-8.750 -0.1262 0.05791 0.05542 -0.1359 0.8164 0.0096
-8.500 -0.1444 0.05346 0.05094 -0.1373 0.8141 0.0095
-8.250 -0.1577 0.05014 0.04757 -0.1366 0.8120 0.0095
-8.000 -0.1604 0.04701 0.04435 -0.1363 0.8102 0.0098
-7.750 -0.1606 0.04364 0.04086 -0.1357 0.8087 0.0099
-7.500 -0.1567 0.04045 0.03753 -0.1349 0.8073 0.0102
-7.250 -0.1494 0.03715 0.03405 -0.1339 0.8058 0.0111
-7.000 -0.1289 0.03472 0.03136 -0.1324 0.8047 0.0124
-6.750 -0.1204 0.03167 0.02807 -0.1308 0.8032 0.0124
-5.500 -0.0405 0.01760 0.01256 -0.1255 0.7957 0.0127
-5.250 -0.0214 0.01284 0.00734 -0.1238 0.7945 0.0095
-5.000 0.0031 0.01174 0.00608 -0.1233 0.7932 0.0092
-4.750 0.0282 0.01109 0.00534 -0.1230 0.7918 0.0093
-4.500 0.0538 0.01057 0.00476 -0.1229 0.7906 0.0097
-4.250 0.0802 0.01016 0.00433 -0.1229 0.7894 0.0102
-4.000 0.1071 0.00985 0.00398 -0.1229 0.7881 0.0112
-3.750 0.1346 0.00965 0.00376 -0.1231 0.7867 0.0124
-3.500 0.1616 0.00924 0.00332 -0.1232 0.7851 0.0155
-3.250 0.1894 0.00900 0.00307 -0.1235 0.7836 0.0223
-3.000 0.2177 0.00887 0.00291 -0.1238 0.7821 0.0271
-2.750 0.2460 0.00872 0.00272 -0.1242 0.7808 0.0324
-2.500 0.2745 0.00858 0.00260 -0.1246 0.7794 0.0397
-2.250 0.3025 0.00837 0.00253 -0.1250 0.7777 0.0878
-2.000 0.3287 0.00755 0.00237 -0.1256 0.7763 0.2963
-1.750 0.3561 0.00665 0.00225 -0.1266 0.7745 0.5480
-1.500 0.3847 0.00630 0.00220 -0.1272 0.7726 0.6545
-1.250 0.4127 0.00611 0.00226 -0.1275 0.7707 0.7324
-1.000 0.4414 0.00613 0.00231 -0.1277 0.7689 0.7663
-0.750 0.4702 0.00619 0.00236 -0.1280 0.7672 0.7859
-0.500 0.4987 0.00630 0.00245 -0.1282 0.7655 0.8015
-0.250 0.5262 0.00647 0.00263 -0.1281 0.7635 0.8158
0.000 0.5542 0.00652 0.00268 -0.1283 0.7615 0.8232
0.250 0.5812 0.00652 0.00272 -0.1282 0.7591 0.8280
0.500 0.6093 0.00653 0.00273 -0.1284 0.7566 0.8325
0.750 0.6385 0.00650 0.00266 -0.1288 0.7531 0.8362
1.000 0.6667 0.00645 0.00258 -0.1290 0.7490 0.8391
1.250 0.6932 0.00641 0.00259 -0.1288 0.7451 0.8429
1.500 0.7210 0.00640 0.00261 -0.1289 0.7415 0.8473
1.750 0.7498 0.00638 0.00257 -0.1293 0.7380 0.8501
2.000 0.7779 0.00635 0.00254 -0.1296 0.7339 0.8520
2.250 0.8052 0.00628 0.00251 -0.1297 0.7279 0.8537
2.500 0.8328 0.00623 0.00247 -0.1298 0.7220 0.8554
2.750 0.8600 0.00620 0.00246 -0.1299 0.7129 0.8572
3.000 0.8864 0.00618 0.00242 -0.1297 0.6992 0.8592
3.250 0.9117 0.00625 0.00241 -0.1294 0.6801 0.8611
3.500 0.9364 0.00639 0.00249 -0.1290 0.6595 0.8629
3.750 0.9611 0.00656 0.00259 -0.1286 0.6425 0.8644
4.000 0.9860 0.00670 0.00270 -0.1283 0.6286 0.8658
4.250 1.0086 0.00691 0.00285 -0.1275 0.6056 0.8675
4.500 1.0267 0.00729 0.00309 -0.1257 0.5678 0.8696
4.750 1.0438 0.00773 0.00337 -0.1239 0.5268 0.8718
5.000 1.0522 0.00854 0.00382 -0.1205 0.4511 0.8741
5.250 1.0583 0.00942 0.00437 -0.1167 0.3824 0.8764
5.500 1.0606 0.01035 0.00495 -0.1123 0.3126 0.8789
5.750 1.0609 0.01112 0.00547 -0.1074 0.2586 0.8818
6.000 1.0628 0.01198 0.00610 -0.1030 0.2067 0.8844
6.250 1.0661 0.01288 0.00679 -0.0991 0.1585 0.8867
6.500 1.0687 0.01392 0.00759 -0.0954 0.1101 0.8894
6.750 1.0746 0.01492 0.00839 -0.0923 0.0704 0.8917
7.000 1.0853 0.01569 0.00906 -0.0901 0.0484 0.8937
7.250 1.0989 0.01636 0.00969 -0.0883 0.0361 0.8952
7.500 1.1132 0.01703 0.01034 -0.0867 0.0287 0.8969
7.750 1.1285 0.01766 0.01099 -0.0853 0.0199 0.8988
8.000 1.1410 0.01850 0.01180 -0.0835 0.0138 0.9006
8.250 1.1565 0.01919 0.01255 -0.0821 0.0122 0.9023
8.500 1.1711 0.01995 0.01336 -0.0808 0.0110 0.9039
8.750 1.1831 0.02088 0.01433 -0.0790 0.0092 0.9059
9.000 1.1932 0.02194 0.01550 -0.0770 0.0082 0.9082
9.250 1.2069 0.02276 0.01639 -0.0756 0.0078 0.9104
9.500 1.2205 0.02362 0.01732 -0.0742 0.0072 0.9130
9.750 1.2329 0.02459 0.01836 -0.0727 0.0066 0.9157
10.000 1.2450 0.02557 0.01940 -0.0712 0.0060 0.9191
10.250 1.2510 0.02698 0.02093 -0.0689 0.0056 0.9242
10.500 1.2456 0.02937 0.02350 -0.0655 0.0052 0.9307
10.750 1.2593 0.03007 0.02429 -0.0641 0.0050 0.9426
11.000 1.2687 0.03119 0.02553 -0.0624 0.0048 1.0000
11.250 1.2796 0.03257 0.02699 -0.0612 0.0046 1.0000
11.500 1.2902 0.03399 0.02848 -0.0601 0.0045 1.0000
11.750 1.3005 0.03549 0.03007 -0.0589 0.0041 1.0000
12.000 1.3131 0.03675 0.03138 -0.0581 0.0040 1.0000
12.250 1.3219 0.03842 0.03314 -0.0570 0.0038 1.0000
12.500 1.3338 0.03977 0.03455 -0.0563 0.0036 1.0000
12.750 1.3413 0.04164 0.03651 -0.0551 0.0035 1.0000
13.000 1.3483 0.04362 0.03858 -0.0541 0.0034 1.0000
13.250 1.3542 0.04575 0.04082 -0.0530 0.0033 1.0000
13.500 1.3583 0.04820 0.04340 -0.0518 0.0033 1.0000
13.750 1.3608 0.05098 0.04633 -0.0507 0.0032 1.0000
14.000 1.3606 0.05427 0.04981 -0.0494 0.0031 1.0000
14.250 1.3592 0.05775 0.05349 -0.0484 0.0031 1.0000
14.500 1.3539 0.06185 0.05783 -0.0475 0.0031 1.0000
14.750 1.3444 0.06654 0.06276 -0.0467 0.0031 1.0000
15.000 1.3340 0.07138 0.06781 -0.0465 0.0031 1.0000
15.250 1.3188 0.07711 0.07378 -0.0466 0.0030 1.0000
15.500 1.3059 0.08255 0.07942 -0.0472 0.0030 1.0000
15.750 1.2880 0.08909 0.08618 -0.0485 0.0030 1.0000
16.000 1.2718 0.09561 0.09289 -0.0503 0.0030 1.0000
16.250 1.2655 0.10057 0.09798 -0.0523 0.0030 1.0000
16.500 1.2465 0.10820 0.10580 -0.0554 0.0030 1.0000
16.750 1.0783 0.11864 0.11660 -0.0631 0.0032 0.9156
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