AH 80-140 (ah80140-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 80-140 (ah80140-il) Reynolds number: 100,000 Max Cl/Cd: 35.68 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah80140-il-100000-n5.txt Download as CSV file: xf-ah80140-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 80-140
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2829 0.10560 0.09935 -0.0377 0.6463 0.0460
-10.000 -0.2706 0.10256 0.09628 -0.0382 0.6431 0.0445
-9.750 -0.2673 0.09858 0.09229 -0.0401 0.6408 0.0435
-9.500 -0.2662 0.09448 0.08819 -0.0423 0.6387 0.0428
-9.250 -0.2644 0.09075 0.08450 -0.0443 0.6359 0.0435
-9.000 -0.2650 0.08662 0.08041 -0.0466 0.6335 0.0433
-8.500 -0.3056 0.07077 0.06466 -0.0590 0.6306 0.0407
-8.250 -0.3131 0.06680 0.06068 -0.0607 0.6283 0.0404
-8.000 -0.3215 0.06213 0.05591 -0.0625 0.6262 0.0402
-7.750 -0.3292 0.05720 0.05080 -0.0638 0.6244 0.0399
-7.500 -0.3341 0.05233 0.04566 -0.0644 0.6226 0.0398
-7.250 -0.3370 0.04732 0.04023 -0.0644 0.6209 0.0399
-7.000 -0.3401 0.04172 0.03391 -0.0636 0.6188 0.0407
-6.750 -0.3189 0.04105 0.03333 -0.0633 0.6155 0.0418
-6.500 -0.3031 0.03902 0.03105 -0.0627 0.6125 0.0429
-6.250 -0.2881 0.03636 0.02796 -0.0617 0.6099 0.0437
-6.000 -0.2709 0.03387 0.02500 -0.0607 0.6075 0.0445
-5.750 -0.2517 0.03156 0.02214 -0.0597 0.6054 0.0456
-5.500 -0.2295 0.03018 0.02047 -0.0590 0.6034 0.0470
-5.250 -0.2058 0.02934 0.01950 -0.0585 0.6014 0.0488
-5.000 -0.1819 0.02813 0.01805 -0.0579 0.5987 0.0508
-4.750 -0.1572 0.02685 0.01646 -0.0573 0.5959 0.0525
-4.500 -0.1322 0.02605 0.01564 -0.0569 0.5930 0.0540
-4.250 -0.1069 0.02537 0.01484 -0.0564 0.5904 0.0569
-4.000 -0.0813 0.02463 0.01394 -0.0559 0.5882 0.0601
-3.750 -0.0558 0.02402 0.01330 -0.0555 0.5860 0.0629
-3.500 -0.0298 0.02345 0.01253 -0.0549 0.5840 0.0669
-3.250 -0.0051 0.02298 0.01216 -0.0545 0.5816 0.0712
-3.000 0.0200 0.02258 0.01173 -0.0539 0.5787 0.0765
-2.750 0.0446 0.02223 0.01146 -0.0534 0.5761 0.0825
-2.500 0.0693 0.02191 0.01115 -0.0529 0.5735 0.0899
-2.250 0.0941 0.02160 0.01082 -0.0523 0.5710 0.0990
-2.000 0.1190 0.02130 0.01051 -0.0516 0.5687 0.1111
-1.750 0.1437 0.02097 0.01024 -0.0510 0.5667 0.1278
-1.500 0.1685 0.02065 0.01003 -0.0504 0.5650 0.1604
-1.250 0.1916 0.02029 0.01004 -0.0498 0.5627 0.2367
-1.000 0.2127 0.01969 0.01016 -0.0491 0.5598 0.4023
-0.750 0.2311 0.01889 0.01047 -0.0468 0.5568 0.6847
-0.500 0.2705 0.01875 0.01070 -0.0477 0.5539 0.8605
-0.250 0.3291 0.01887 0.01073 -0.0529 0.5513 0.9387
0.000 0.4069 0.01896 0.01058 -0.0623 0.5488 0.9902
0.250 0.4419 0.01910 0.01053 -0.0640 0.5468 1.0000
0.500 0.4613 0.01939 0.01076 -0.0628 0.5439 1.0000
0.750 0.4804 0.01976 0.01112 -0.0617 0.5401 1.0000
1.000 0.5007 0.02007 0.01137 -0.0606 0.5368 1.0000
1.250 0.5222 0.02032 0.01153 -0.0596 0.5340 1.0000
1.500 0.5446 0.02053 0.01164 -0.0587 0.5316 1.0000
1.750 0.5679 0.02072 0.01172 -0.0578 0.5295 1.0000
2.000 0.5918 0.02090 0.01179 -0.0570 0.5277 1.0000
2.250 0.6102 0.02155 0.01251 -0.0560 0.5232 1.0000
2.500 0.6308 0.02205 0.01303 -0.0551 0.5194 1.0000
2.750 0.6529 0.02244 0.01339 -0.0543 0.5165 1.0000
3.000 0.6763 0.02271 0.01362 -0.0536 0.5139 1.0000
3.250 0.7009 0.02290 0.01374 -0.0529 0.5117 1.0000
3.500 0.7264 0.02305 0.01381 -0.0523 0.5098 1.0000
3.750 0.7435 0.02392 0.01479 -0.0513 0.5048 1.0000
4.000 0.7629 0.02460 0.01554 -0.0505 0.5005 1.0000
4.250 0.7856 0.02497 0.01591 -0.0498 0.4972 1.0000
4.500 0.8104 0.02516 0.01607 -0.0492 0.4946 1.0000
4.750 0.8369 0.02522 0.01609 -0.0487 0.4925 1.0000
5.000 0.8554 0.02596 0.01691 -0.0478 0.4881 1.0000
5.250 0.8706 0.02696 0.01803 -0.0468 0.4822 1.0000
5.500 0.8934 0.02730 0.01840 -0.0461 0.4789 1.0000
5.750 0.9191 0.02740 0.01850 -0.0456 0.4765 1.0000
6.000 0.9467 0.02737 0.01845 -0.0452 0.4746 1.0000
6.250 0.9508 0.02921 0.02050 -0.0436 0.4666 1.0000
6.500 0.9710 0.02972 0.02107 -0.0428 0.4626 1.0000
6.750 0.9982 0.02957 0.02094 -0.0423 0.4599 1.0000
7.000 1.0294 0.02909 0.02044 -0.0420 0.4578 1.0000
7.250 1.0243 0.03136 0.02292 -0.0398 0.4477 1.0000
7.500 1.0505 0.03119 0.02278 -0.0392 0.4445 1.0000
7.750 1.0828 0.03055 0.02216 -0.0389 0.4422 1.0000
8.000 1.0695 0.03324 0.02503 -0.0362 0.4316 1.0000
8.250 1.0987 0.03268 0.02451 -0.0356 0.4283 1.0000
8.500 1.1337 0.03177 0.02364 -0.0354 0.4260 1.0000
9.000 1.1321 0.03483 0.02689 -0.0310 0.4116 1.0000
9.500 1.0956 0.04217 0.03433 -0.0290 0.3913 1.0000
10.000 1.1344 0.04255 0.03486 -0.0274 0.3809 1.0000
10.500 1.1524 0.04516 0.03759 -0.0262 0.3654 1.0000
11.000 1.1700 0.04793 0.04051 -0.0251 0.3499 1.0000
11.500 1.1929 0.05008 0.04279 -0.0240 0.3342 1.0000
11.750 1.1850 0.05341 0.04618 -0.0238 0.3226 1.0000
12.000 1.2196 0.05164 0.04445 -0.0227 0.3156 1.0000
12.250 1.2179 0.05421 0.04706 -0.0224 0.3038 1.0000
12.500 1.2154 0.05693 0.04983 -0.0223 0.2918 1.0000
12.750 1.2230 0.05839 0.05132 -0.0218 0.2800 1.0000
13.000 1.2318 0.05966 0.05257 -0.0213 0.2671 1.0000
13.250 1.2367 0.06139 0.05426 -0.0210 0.2531 1.0000
13.500 1.2382 0.06367 0.05650 -0.0208 0.2387 1.0000
13.750 1.2385 0.06623 0.05901 -0.0208 0.2250 1.0000
14.000 1.2372 0.06910 0.06185 -0.0209 0.2115 1.0000
14.250 1.2355 0.07213 0.06488 -0.0212 0.1994 1.0000
14.500 1.2341 0.07519 0.06795 -0.0215 0.1880 1.0000
14.750 1.2327 0.07831 0.07106 -0.0219 0.1769 1.0000
15.000 1.2309 0.08150 0.07423 -0.0223 0.1661 1.0000
15.250 1.2277 0.08505 0.07782 -0.0230 0.1558 1.0000
15.500 1.2246 0.08864 0.08144 -0.0237 0.1458 1.0000
15.750 1.2210 0.09235 0.08517 -0.0245 0.1361 1.0000
16.000 1.2156 0.09640 0.08922 -0.0255 0.1257 1.0000
16.250 1.2093 0.10066 0.09347 -0.0267 0.1152 1.0000
16.500 1.2042 0.10483 0.09768 -0.0279 0.1060 1.0000
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