AH 88-K-130/20 (ah88k130-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 88-K-130/20 (ah88k130-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.2 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah88k130-il-1000000-n5.txt Download as CSV file: xf-ah88k130-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1412 0.08426 0.08146 -0.1149 0.7945 0.0041
-10.250 -0.1403 0.08028 0.07749 -0.1168 0.7936 0.0039
-10.000 -0.1419 0.07581 0.07303 -0.1191 0.7926 0.0040
-9.500 -0.1517 0.06586 0.06314 -0.1246 0.7909 0.0041
-9.250 -0.1608 0.06012 0.05744 -0.1290 0.7900 0.0042
-9.000 -0.1859 0.05324 0.05056 -0.1341 0.7884 0.0039
-8.750 -0.2053 0.04957 0.04685 -0.1334 0.7869 0.0041
-8.500 -0.2195 0.04472 0.04189 -0.1329 0.7855 0.0041
-8.250 -0.2306 0.03935 0.03632 -0.1316 0.7840 0.0042
-8.000 -0.2363 0.03376 0.03046 -0.1296 0.7824 0.0045
-7.750 -0.2603 0.02244 0.01832 -0.1246 0.7803 0.0047
-7.500 -0.2490 0.01882 0.01421 -0.1229 0.7789 0.0048
-7.250 -0.2295 0.01693 0.01201 -0.1221 0.7778 0.0048
-7.000 -0.2060 0.01598 0.01088 -0.1219 0.7770 0.0050
-6.750 -0.1822 0.01501 0.00976 -0.1216 0.7762 0.0051
-6.500 -0.1577 0.01419 0.00880 -0.1214 0.7749 0.0052
-6.250 -0.1336 0.01322 0.00767 -0.1210 0.7735 0.0052
-6.000 -0.1089 0.01244 0.00677 -0.1208 0.7720 0.0052
-5.750 -0.0837 0.01177 0.00599 -0.1206 0.7707 0.0053
-5.500 -0.0581 0.01123 0.00537 -0.1205 0.7695 0.0053
-5.250 -0.0330 0.01057 0.00460 -0.1204 0.7684 0.0054
-5.000 -0.0072 0.01004 0.00398 -0.1203 0.7672 0.0057
-4.750 0.0195 0.00968 0.00356 -0.1204 0.7661 0.0060
-4.500 0.0468 0.00941 0.00325 -0.1206 0.7649 0.0066
-4.250 0.0743 0.00920 0.00300 -0.1208 0.7636 0.0072
-4.000 0.1019 0.00899 0.00276 -0.1210 0.7627 0.0078
-3.750 0.1297 0.00880 0.00256 -0.1213 0.7616 0.0087
-3.500 0.1575 0.00862 0.00240 -0.1216 0.7603 0.0111
-3.250 0.1854 0.00845 0.00228 -0.1219 0.7588 0.0159
-3.000 0.2136 0.00835 0.00217 -0.1222 0.7573 0.0189
-2.750 0.2417 0.00820 0.00202 -0.1225 0.7558 0.0236
-2.500 0.2700 0.00810 0.00191 -0.1229 0.7544 0.0262
-2.250 0.2984 0.00800 0.00180 -0.1232 0.7530 0.0308
-2.000 0.3266 0.00784 0.00171 -0.1236 0.7515 0.0539
-1.750 0.3548 0.00766 0.00162 -0.1241 0.7500 0.0932
-1.500 0.3828 0.00739 0.00155 -0.1246 0.7483 0.1609
-1.250 0.4108 0.00696 0.00148 -0.1252 0.7464 0.2806
-1.000 0.4391 0.00656 0.00142 -0.1260 0.7442 0.3968
-0.500 0.4971 0.00561 0.00137 -0.1276 0.7401 0.6977
-0.250 0.5248 0.00559 0.00155 -0.1277 0.7381 0.7733
0.000 0.5535 0.00564 0.00158 -0.1280 0.7361 0.7863
0.250 0.5825 0.00567 0.00161 -0.1285 0.7336 0.7946
0.500 0.6108 0.00569 0.00165 -0.1288 0.7302 0.7990
0.750 0.6391 0.00568 0.00163 -0.1290 0.7243 0.8026
1.000 0.6672 0.00568 0.00161 -0.1293 0.7151 0.8059
1.250 0.6951 0.00570 0.00160 -0.1295 0.7076 0.8102
1.500 0.7226 0.00574 0.00165 -0.1296 0.7000 0.8142
1.750 0.7500 0.00578 0.00167 -0.1297 0.6913 0.8168
2.000 0.7770 0.00585 0.00170 -0.1297 0.6807 0.8186
2.250 0.8034 0.00596 0.00174 -0.1297 0.6667 0.8203
2.500 0.8291 0.00610 0.00182 -0.1295 0.6505 0.8219
2.750 0.8540 0.00627 0.00192 -0.1291 0.6325 0.8234
3.000 0.8767 0.00652 0.00207 -0.1283 0.6061 0.8250
3.250 0.8971 0.00688 0.00227 -0.1271 0.5712 0.8265
3.500 0.9163 0.00730 0.00251 -0.1257 0.5296 0.8280
3.750 0.9316 0.00790 0.00286 -0.1236 0.4689 0.8296
4.000 0.9447 0.00860 0.00327 -0.1211 0.4095 0.8315
4.250 0.9573 0.00930 0.00370 -0.1185 0.3526 0.8337
4.500 0.9665 0.01010 0.00419 -0.1154 0.2889 0.8358
4.750 0.9682 0.01102 0.00475 -0.1108 0.2156 0.8379
5.000 0.9692 0.01189 0.00535 -0.1062 0.1528 0.8403
5.250 0.9773 0.01259 0.00588 -0.1029 0.1127 0.8426
5.500 0.9876 0.01325 0.00641 -0.1002 0.0812 0.8449
5.750 0.9997 0.01388 0.00693 -0.0979 0.0567 0.8473
6.250 1.0315 0.01490 0.00787 -0.0947 0.0356 0.8505
6.500 1.0488 0.01535 0.00833 -0.0934 0.0323 0.8517
6.750 1.0664 0.01580 0.00881 -0.0922 0.0282 0.8530
7.000 1.0849 0.01621 0.00926 -0.0911 0.0268 0.8541
7.250 1.1027 0.01669 0.00977 -0.0900 0.0231 0.8552
7.500 1.1150 0.01748 0.01050 -0.0881 0.0123 0.8564
7.750 1.1307 0.01811 0.01115 -0.0867 0.0102 0.8576
8.000 1.1466 0.01875 0.01183 -0.0854 0.0087 0.8588
8.250 1.1632 0.01935 0.01247 -0.0843 0.0081 0.8600
8.500 1.1795 0.01999 0.01315 -0.0831 0.0075 0.8612
8.750 1.1953 0.02066 0.01386 -0.0819 0.0066 0.8624
9.000 1.2099 0.02144 0.01467 -0.0806 0.0058 0.8636
9.500 1.2388 0.02303 0.01636 -0.0779 0.0049 0.8666
9.750 1.2537 0.02380 0.01721 -0.0767 0.0046 0.8681
10.000 1.2687 0.02458 0.01803 -0.0756 0.0042 0.8696
10.250 1.2826 0.02545 0.01895 -0.0744 0.0038 0.8713
10.500 1.2959 0.02638 0.01994 -0.0731 0.0036 0.8730
10.750 1.3079 0.02744 0.02105 -0.0717 0.0032 0.8749
11.000 1.3180 0.02867 0.02235 -0.0702 0.0030 0.8767
11.250 1.3306 0.02972 0.02347 -0.0690 0.0029 0.8786
11.500 1.3421 0.03085 0.02469 -0.0677 0.0028 0.8808
11.750 1.3549 0.03191 0.02581 -0.0666 0.0026 0.8833
12.000 1.3649 0.03322 0.02721 -0.0653 0.0025 0.8861
12.250 1.3753 0.03454 0.02863 -0.0641 0.0024 0.8889
12.500 1.3872 0.03575 0.02990 -0.0631 0.0022 0.8916
12.750 1.3965 0.03719 0.03143 -0.0619 0.0022 0.8946
13.000 1.4070 0.03854 0.03286 -0.0609 0.0020 0.8982
13.250 1.4173 0.03992 0.03431 -0.0599 0.0019 0.9024
13.500 1.4250 0.04156 0.03606 -0.0588 0.0019 0.9074
13.750 1.4323 0.04318 0.03778 -0.0576 0.0018 0.9152
14.000 1.4317 0.04510 0.03991 -0.0554 0.0017 0.9725
14.250 1.4327 0.04767 0.04261 -0.0542 0.0016 1.0000
14.500 1.4340 0.05032 0.04538 -0.0532 0.0015 1.0000
14.750 1.4394 0.05257 0.04774 -0.0526 0.0015 1.0000
15.000 1.4437 0.05500 0.05030 -0.0520 0.0015 1.0000
15.250 1.4474 0.05754 0.05295 -0.0516 0.0015 1.0000
15.500 1.4485 0.06048 0.05602 -0.0511 0.0015 1.0000
15.750 1.4499 0.06347 0.05913 -0.0509 0.0015 1.0000
16.000 1.4508 0.06660 0.06239 -0.0508 0.0015 1.0000
16.250 1.4501 0.07001 0.06593 -0.0509 0.0014 1.0000
16.500 1.4475 0.07377 0.06984 -0.0511 0.0014 1.0000
16.750 1.4443 0.07776 0.07396 -0.0516 0.0014 1.0000
17.000 1.4399 0.08201 0.07836 -0.0523 0.0014 1.0000
17.250 1.4338 0.08668 0.08317 -0.0532 0.0014 1.0000
17.500 1.4267 0.09161 0.08826 -0.0545 0.0014 1.0000
17.750 1.4182 0.09693 0.09373 -0.0561 0.0014 1.0000
18.000 1.4080 0.10274 0.09970 -0.0582 0.0014 1.0000
18.250 1.3970 0.10888 0.10600 -0.0606 0.0013 1.0000
18.500 1.3848 0.11547 0.11275 -0.0636 0.0013 1.0000
18.750 1.3711 0.12253 0.11996 -0.0670 0.0013 1.0000
19.000 1.3567 0.12998 0.12757 -0.0710 0.0013 1.0000
19.250 1.3404 0.13814 0.13590 -0.0756 0.0013 1.0000
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Polar data table (+)
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