AH 88-K-130/20 (ah88k130-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 88-K-130/20 (ah88k130-il) Reynolds number: 200,000 Max Cl/Cd: 78.96 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah88k130-il-200000-n5.txt Download as CSV file: xf-ah88k130-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0785 0.09341 0.08934 -0.1037 0.8674 0.0208
-11.000 -0.0757 0.08986 0.08580 -0.1049 0.8662 0.0209
-10.500 -0.1332 0.09154 0.08725 -0.1151 0.8732 0.0197
-10.000 -0.1239 0.08482 0.08052 -0.1179 0.8691 0.0175
-9.750 -0.1218 0.08127 0.07699 -0.1195 0.8672 0.0173
-9.500 -0.1158 0.07953 0.07528 -0.1201 0.8655 0.0224
-9.000 -0.1222 0.06944 0.06521 -0.1261 0.8609 0.0172
-8.750 -0.1286 0.06406 0.05988 -0.1309 0.8580 0.0177
-8.500 -0.1367 0.06038 0.05619 -0.1325 0.8553 0.0172
-8.250 -0.1487 0.05726 0.05304 -0.1325 0.8521 0.0168
-8.000 -0.1567 0.05391 0.04958 -0.1326 0.8495 0.0168
-7.750 -0.1605 0.05054 0.04607 -0.1323 0.8474 0.0163
-7.500 -0.1623 0.04730 0.04270 -0.1315 0.8444 0.0157
-7.250 -0.1620 0.04370 0.03889 -0.1304 0.8413 0.0151
-7.000 -0.1587 0.03973 0.03462 -0.1290 0.8385 0.0144
-6.750 -0.1538 0.03479 0.02917 -0.1271 0.8362 0.0135
-6.500 -0.1422 0.03074 0.02454 -0.1253 0.8343 0.0129
-6.250 -0.1256 0.02827 0.02165 -0.1242 0.8325 0.0128
-6.000 -0.1084 0.02625 0.01931 -0.1230 0.8299 0.0128
-5.750 -0.0885 0.02447 0.01722 -0.1221 0.8276 0.0130
-5.500 -0.0665 0.02302 0.01550 -0.1215 0.8255 0.0133
-5.250 -0.0428 0.02181 0.01409 -0.1210 0.8235 0.0138
-5.000 -0.0179 0.02072 0.01280 -0.1207 0.8217 0.0145
-4.750 0.0077 0.01971 0.01162 -0.1203 0.8201 0.0153
-4.500 0.0318 0.01911 0.01090 -0.1198 0.8180 0.0173
-4.250 0.0535 0.01848 0.01020 -0.1189 0.8150 0.0191
-4.000 0.0755 0.01766 0.00935 -0.1182 0.8123 0.0210
-3.750 0.0996 0.01706 0.00869 -0.1178 0.8101 0.0236
-3.500 0.1252 0.01655 0.00806 -0.1176 0.8082 0.0272
-3.250 0.1514 0.01606 0.00754 -0.1177 0.8066 0.0360
-3.000 0.1775 0.01573 0.00718 -0.1177 0.8047 0.0470
-2.750 0.1991 0.01552 0.00699 -0.1169 0.8011 0.0634
-2.500 0.2225 0.01495 0.00677 -0.1168 0.7982 0.1500
-2.250 0.2461 0.01391 0.00654 -0.1171 0.7959 0.3834
-2.000 0.2683 0.01310 0.00658 -0.1164 0.7939 0.6261
-1.750 0.2852 0.01322 0.00707 -0.1130 0.7922 0.7431
-1.500 0.3037 0.01370 0.00756 -0.1106 0.7887 0.8034
-1.250 0.3178 0.01412 0.00800 -0.1071 0.7849 0.8332
-1.000 0.3381 0.01427 0.00809 -0.1052 0.7822 0.8491
-0.750 0.3614 0.01429 0.00804 -0.1040 0.7801 0.8577
-0.500 0.3906 0.01425 0.00790 -0.1044 0.7785 0.8641
-0.250 0.4102 0.01437 0.00800 -0.1030 0.7746 0.8687
0.000 0.4322 0.01447 0.00807 -0.1021 0.7707 0.8736
0.250 0.4601 0.01447 0.00801 -0.1024 0.7681 0.8783
0.500 0.4871 0.01441 0.00790 -0.1023 0.7660 0.8815
0.750 0.5161 0.01433 0.00778 -0.1027 0.7643 0.8849
1.000 0.5352 0.01454 0.00800 -0.1015 0.7591 0.8898
1.250 0.5589 0.01460 0.00807 -0.1010 0.7555 0.8935
1.500 0.5852 0.01456 0.00802 -0.1008 0.7530 0.8967
1.750 0.6143 0.01448 0.00793 -0.1012 0.7511 0.8999
2.000 0.6377 0.01459 0.00806 -0.1008 0.7471 0.9041
2.250 0.6554 0.01472 0.00825 -0.0991 0.7419 0.9080
2.500 0.6812 0.01469 0.00824 -0.0989 0.7391 0.9115
2.750 0.7105 0.01461 0.00818 -0.0993 0.7371 0.9146
3.000 0.7275 0.01482 0.00846 -0.0977 0.7309 0.9188
3.250 0.7506 0.01477 0.00848 -0.0970 0.7265 0.9221
3.500 0.7796 0.01460 0.00835 -0.0973 0.7238 0.9253
3.750 0.7956 0.01480 0.00863 -0.0954 0.7172 0.9307
4.000 0.8198 0.01471 0.00861 -0.0948 0.7128 0.9347
4.250 0.8460 0.01447 0.00845 -0.0945 0.7072 0.9382
4.500 0.8682 0.01433 0.00838 -0.0935 0.6989 0.9423
4.750 0.8903 0.01419 0.00831 -0.0925 0.6896 0.9465
5.000 0.9190 0.01383 0.00801 -0.0926 0.6801 0.9499
5.250 0.9463 0.01363 0.00789 -0.0924 0.6701 0.9543
5.750 1.0002 0.01327 0.00759 -0.0920 0.6379 0.9645
6.000 1.0268 0.01324 0.00757 -0.0919 0.6166 0.9711
6.250 1.0517 0.01332 0.00757 -0.0915 0.5843 0.9824
6.500 1.0692 0.01362 0.00781 -0.0900 0.5476 1.0000
6.750 1.0765 0.01431 0.00824 -0.0868 0.4872 1.0000
7.000 1.0721 0.01558 0.00910 -0.0821 0.4176 1.0000
7.250 1.0636 0.01729 0.01040 -0.0774 0.3473 1.0000
7.500 1.0582 0.01909 0.01184 -0.0736 0.2816 1.0000
7.750 1.0540 0.02102 0.01338 -0.0702 0.2131 1.0000
8.000 1.0517 0.02298 0.01493 -0.0672 0.1457 1.0000
8.250 1.0539 0.02474 0.01638 -0.0649 0.0948 1.0000
8.500 1.0613 0.02621 0.01769 -0.0631 0.0633 1.0000
8.750 1.0709 0.02755 0.01900 -0.0616 0.0452 1.0000
9.000 1.0806 0.02894 0.02035 -0.0601 0.0331 1.0000
9.250 1.0902 0.03035 0.02179 -0.0586 0.0253 1.0000
9.500 1.1014 0.03167 0.02320 -0.0573 0.0205 1.0000
9.750 1.1104 0.03318 0.02479 -0.0558 0.0183 1.0000
10.000 1.1214 0.03455 0.02627 -0.0546 0.0165 1.0000
10.250 1.1321 0.03595 0.02773 -0.0535 0.0145 1.0000
10.500 1.1370 0.03791 0.02974 -0.0519 0.0130 1.0000
10.750 1.1459 0.03957 0.03154 -0.0506 0.0124 1.0000
11.000 1.1536 0.04138 0.03353 -0.0493 0.0117 1.0000
11.250 1.1617 0.04324 0.03551 -0.0480 0.0111 1.0000
11.500 1.1702 0.04513 0.03753 -0.0469 0.0106 1.0000
11.750 1.1795 0.04700 0.03951 -0.0458 0.0099 1.0000
12.000 1.1890 0.04888 0.04149 -0.0449 0.0094 1.0000
12.250 1.1966 0.05110 0.04379 -0.0439 0.0087 1.0000
12.500 1.2065 0.05325 0.04611 -0.0430 0.0080 1.0000
12.750 1.2172 0.05533 0.04839 -0.0422 0.0077 1.0000
13.000 1.2268 0.05766 0.05095 -0.0413 0.0074 1.0000
13.250 1.2344 0.06033 0.05386 -0.0405 0.0072 1.0000
13.500 1.2393 0.06331 0.05709 -0.0397 0.0070 1.0000
13.750 1.2407 0.06664 0.06074 -0.0389 0.0068 1.0000
14.000 1.2389 0.07035 0.06473 -0.0384 0.0067 1.0000
14.250 1.2342 0.07445 0.06910 -0.0380 0.0065 1.0000
14.500 1.2266 0.07898 0.07391 -0.0380 0.0065 1.0000
14.750 1.2164 0.08396 0.07916 -0.0383 0.0064 1.0000
15.000 1.2040 0.08940 0.08487 -0.0392 0.0064 1.0000
15.250 1.1895 0.09542 0.09116 -0.0406 0.0064 1.0000
15.500 1.1734 0.10195 0.09794 -0.0427 0.0064 1.0000
15.750 1.1557 0.10914 0.10538 -0.0456 0.0064 1.0000
16.000 1.1370 0.11702 0.11349 -0.0494 0.0064 1.0000
16.250 1.1172 0.12576 0.12245 -0.0543 0.0065 1.0000
16.500 1.0965 0.13552 0.13241 -0.0602 0.0066 1.0000
16.750 1.0745 0.14675 0.14382 -0.0675 0.0067 1.0000
17.000 1.0495 0.16073 0.15792 -0.0766 0.0069 1.0000
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