AH 80-136 (ah80136-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 80-136 (ah80136-il) Reynolds number: 200,000 Max Cl/Cd: 70.99 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah80136-il-200000.txt Download as CSV file: xf-ah80136-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 80-136
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5140 0.11687 0.11331 0.0275 0.6961 0.0392
-9.250 -0.5127 0.11240 0.10887 0.0242 0.6943 0.0404
-9.000 -0.5143 0.10735 0.10386 0.0185 0.6928 0.0417
-8.750 -0.4079 0.09049 0.08713 0.0019 0.6864 0.0444
-8.500 -0.4017 0.08705 0.08373 0.0017 0.6842 0.0454
-8.250 -0.4009 0.08300 0.07970 0.0003 0.6824 0.0463
-8.000 -0.4040 0.07839 0.07512 -0.0020 0.6807 0.0471
-7.750 -0.4113 0.07312 0.06987 -0.0056 0.6793 0.0478
-7.500 -0.4276 0.06657 0.06331 -0.0120 0.6781 0.0477
-7.250 -0.4407 0.06156 0.05823 -0.0139 0.6767 0.0481
-7.000 -0.4458 0.05650 0.05305 -0.0156 0.6753 0.0492
-6.750 -0.4473 0.05143 0.04781 -0.0167 0.6738 0.0509
-6.500 -0.4485 0.04743 0.04314 -0.0173 0.6725 0.0551
-6.250 -0.4824 0.05823 0.05330 -0.0124 0.6735 0.0552
-6.000 -0.4754 0.05072 0.04571 -0.0130 0.6722 0.0571
-5.750 -0.4549 0.04784 0.04290 -0.0138 0.6694 0.0592
-5.500 -0.4338 0.04549 0.04041 -0.0142 0.6667 0.0634
-5.250 -0.3822 0.02651 0.02164 -0.0184 0.6616 0.0739
-5.000 -0.3659 0.02359 0.01831 -0.0177 0.6598 0.0852
-4.750 -0.3461 0.02145 0.01615 -0.0172 0.6581 0.0899
-4.500 -0.3390 0.03190 0.02451 -0.0099 0.6593 0.0432
-4.250 -0.3143 0.02852 0.02087 -0.0093 0.6577 0.0409
-4.000 -0.2849 0.02665 0.01871 -0.0095 0.6548 0.0409
-3.750 -0.2553 0.02551 0.01728 -0.0098 0.6520 0.0436
-3.500 -0.2273 0.02368 0.01539 -0.0100 0.6496 0.0461
-3.250 -0.1995 0.02268 0.01431 -0.0099 0.6475 0.0486
-3.000 -0.1724 0.02205 0.01358 -0.0095 0.6456 0.0534
-2.750 -0.1467 0.02106 0.01250 -0.0088 0.6439 0.0569
-2.500 -0.1211 0.02032 0.01179 -0.0085 0.6421 0.0626
-2.250 -0.0907 0.02008 0.01160 -0.0098 0.6385 0.0703
-2.000 -0.0629 0.01969 0.01124 -0.0102 0.6355 0.0810
-1.750 -0.0367 0.01914 0.01082 -0.0101 0.6331 0.1130
-1.500 -0.0282 0.01648 0.01052 -0.0072 0.6312 0.6542
-1.250 -0.0045 0.01609 0.01084 -0.0041 0.6297 0.8808
-1.000 0.0372 0.01642 0.01104 -0.0054 0.6284 0.9463
-0.750 0.1256 0.01724 0.01173 -0.0173 0.6240 0.9823
-0.500 0.2026 0.01745 0.01177 -0.0272 0.6206 1.0000
-0.250 0.2270 0.01756 0.01177 -0.0273 0.6182 1.0000
0.000 0.2502 0.01757 0.01167 -0.0268 0.6162 1.0000
0.250 0.2725 0.01755 0.01153 -0.0260 0.6146 1.0000
0.500 0.2967 0.01774 0.01163 -0.0257 0.6125 1.0000
0.750 0.3270 0.01851 0.01245 -0.0281 0.6067 1.0000
1.000 0.3512 0.01867 0.01255 -0.0278 0.6038 1.0000
1.250 0.3742 0.01869 0.01248 -0.0270 0.6017 1.0000
1.500 0.3968 0.01865 0.01235 -0.0259 0.6001 1.0000
1.750 0.4192 0.01863 0.01224 -0.0247 0.5987 1.0000
2.000 0.4490 0.01973 0.01346 -0.0274 0.5908 1.0000
2.250 0.4724 0.01974 0.01342 -0.0265 0.5882 1.0000
2.500 0.4955 0.01961 0.01323 -0.0253 0.5864 1.0000
2.750 0.5186 0.01947 0.01301 -0.0240 0.5849 1.0000
3.000 0.5456 0.02061 0.01427 -0.0260 0.5773 1.0000
3.250 0.5697 0.02067 0.01432 -0.0254 0.5743 1.0000
3.500 0.5937 0.02051 0.01411 -0.0243 0.5724 1.0000
3.750 0.6178 0.02030 0.01387 -0.0231 0.5709 1.0000
4.000 0.6429 0.02141 0.01509 -0.0246 0.5636 1.0000
4.250 0.6676 0.02146 0.01515 -0.0240 0.5602 1.0000
4.500 0.6925 0.02123 0.01489 -0.0230 0.5582 1.0000
4.750 0.7177 0.02092 0.01458 -0.0219 0.5566 1.0000
5.000 0.7429 0.02071 0.01434 -0.0209 0.5549 1.0000
5.250 0.7671 0.02187 0.01567 -0.0224 0.5458 1.0000
5.500 0.7932 0.02150 0.01530 -0.0215 0.5438 1.0000
5.750 0.8196 0.02110 0.01491 -0.0205 0.5421 1.0000
6.000 0.8434 0.02200 0.01597 -0.0214 0.5340 1.0000
6.250 0.8702 0.02166 0.01565 -0.0207 0.5310 1.0000
6.500 0.8976 0.02113 0.01514 -0.0198 0.5288 1.0000
6.750 0.9254 0.02048 0.01448 -0.0188 0.5270 1.0000
7.000 0.9499 0.02111 0.01531 -0.0196 0.5178 1.0000
7.250 0.9782 0.02044 0.01466 -0.0188 0.5149 1.0000
7.500 1.0068 0.01974 0.01396 -0.0178 0.5127 1.0000
7.750 1.0320 0.02006 0.01449 -0.0184 0.5030 1.0000
8.000 1.0622 0.01876 0.01313 -0.0171 0.4989 1.0000
8.250 1.0893 0.01832 0.01284 -0.0171 0.4876 1.0000
8.500 1.1169 0.01783 0.01247 -0.0169 0.4765 1.0000
8.750 1.1446 0.01735 0.01208 -0.0167 0.4637 1.0000
9.000 1.1716 0.01706 0.01188 -0.0166 0.4475 1.0000
9.250 1.1979 0.01690 0.01173 -0.0165 0.4274 1.0000
9.500 1.2218 0.01721 0.01204 -0.0168 0.3969 1.0000
9.750 1.2416 0.01801 0.01271 -0.0171 0.3574 1.0000
10.000 1.2545 0.01970 0.01421 -0.0178 0.3106 1.0000
10.250 1.2566 0.02283 0.01711 -0.0200 0.2613 1.0000
10.500 1.2439 0.02634 0.02037 -0.0200 0.2180 1.0000
10.750 1.2261 0.03027 0.02399 -0.0194 0.1742 1.0000
11.000 1.2068 0.03435 0.02775 -0.0187 0.1298 1.0000
11.250 1.1885 0.03838 0.03147 -0.0179 0.0946 1.0000
11.500 1.1749 0.04206 0.03496 -0.0172 0.0739 1.0000
11.750 1.1642 0.04556 0.03840 -0.0166 0.0614 1.0000
12.000 1.1569 0.04897 0.04180 -0.0162 0.0519 1.0000
12.250 1.1485 0.05258 0.04540 -0.0159 0.0455 1.0000
12.500 1.1461 0.05564 0.04850 -0.0157 0.0397 1.0000
12.750 1.1402 0.05904 0.05191 -0.0153 0.0359 1.0000
13.000 1.1421 0.06169 0.05464 -0.0151 0.0326 1.0000
13.250 1.1428 0.06443 0.05743 -0.0148 0.0301 1.0000
13.500 1.1424 0.06683 0.05978 -0.0135 0.0278 1.0000
13.750 1.1491 0.06902 0.06210 -0.0133 0.0260 1.0000
14.000 1.1546 0.07130 0.06446 -0.0131 0.0241 1.0000
14.250 1.1601 0.07349 0.06667 -0.0128 0.0227 1.0000
14.500 1.1684 0.07494 0.06810 -0.0113 0.0215 1.0000
14.750 1.1821 0.07567 0.06890 -0.0086 0.0205 1.0000
15.000 1.1899 0.07779 0.07119 -0.0079 0.0200 1.0000
15.250 1.1969 0.08008 0.07366 -0.0071 0.0196 1.0000
15.500 1.2014 0.08278 0.07656 -0.0065 0.0192 1.0000
15.750 1.2030 0.08600 0.07998 -0.0062 0.0190 1.0000
16.000 1.2010 0.08977 0.08401 -0.0064 0.0188 1.0000
16.250 1.1960 0.09403 0.08849 -0.0071 0.0186 1.0000
16.500 1.1884 0.09875 0.09342 -0.0082 0.0185 1.0000
16.750 1.1785 0.10392 0.09881 -0.0098 0.0184 1.0000
17.000 1.1667 0.10958 0.10469 -0.0119 0.0183 1.0000
17.250 1.1531 0.11575 0.11108 -0.0145 0.0182 1.0000
17.500 1.1371 0.12260 0.11814 -0.0177 0.0183 1.0000
17.750 1.1196 0.13007 0.12582 -0.0215 0.0184 1.0000
18.000 1.1004 0.13834 0.13431 -0.0261 0.0186 1.0000
18.250 1.0795 0.14748 0.14363 -0.0314 0.0190 1.0000
18.500 1.0579 0.15739 0.15371 -0.0375 0.0194 1.0000
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