AH 80-136 (ah80136-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 80-136 (ah80136-il) Reynolds number: 50,000 Max Cl/Cd: 13.82 at α=12.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah80136-il-50000-n5.txt Download as CSV file: xf-ah80136-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3347 0.10466 0.09906 -0.0134 0.7501 0.0658
-9.250 -0.3335 0.10041 0.09482 -0.0149 0.7480 0.0642
-9.000 -0.4700 0.10270 0.09692 -0.0114 0.7560 0.0550
-8.750 -0.4584 0.09912 0.09334 -0.0110 0.7527 0.0537
-8.500 -0.4546 0.09430 0.08853 -0.0146 0.7498 0.0528
-8.250 -0.4540 0.08903 0.08324 -0.0195 0.7472 0.0520
-8.000 -0.4582 0.08451 0.07867 -0.0227 0.7450 0.0513
-7.750 -0.4587 0.07966 0.07372 -0.0264 0.7425 0.0507
-7.500 -0.4571 0.07489 0.06881 -0.0297 0.7395 0.0504
-7.250 -0.4537 0.07043 0.06414 -0.0321 0.7366 0.0503
-7.000 -0.4484 0.06622 0.05966 -0.0336 0.7339 0.0502
-6.750 -0.4410 0.06226 0.05537 -0.0344 0.7313 0.0501
-6.500 -0.4301 0.05841 0.05113 -0.0350 0.7287 0.0498
-6.250 -0.4145 0.05464 0.04694 -0.0360 0.7254 0.0493
-6.000 -0.3974 0.05130 0.04313 -0.0363 0.7224 0.0492
-5.750 -0.3791 0.04833 0.03967 -0.0361 0.7196 0.0494
-5.500 -0.3597 0.04580 0.03661 -0.0354 0.7170 0.0508
-5.250 -0.3376 0.04363 0.03385 -0.0350 0.7142 0.0534
-5.000 -0.3110 0.04173 0.03132 -0.0353 0.7105 0.0553
-4.750 -0.2852 0.03946 0.02885 -0.0356 0.7074 0.0569
-4.500 -0.2591 0.03785 0.02704 -0.0355 0.7046 0.0595
-4.250 -0.2332 0.03666 0.02560 -0.0351 0.7021 0.0647
-4.000 -0.2039 0.03559 0.02413 -0.0352 0.6991 0.0689
-3.750 -0.1748 0.03439 0.02298 -0.0360 0.6954 0.0735
-3.500 -0.1471 0.03373 0.02210 -0.0361 0.6923 0.0822
-3.250 -0.1216 0.03293 0.02127 -0.0359 0.6895 0.0901
-3.000 -0.0972 0.03229 0.02048 -0.0354 0.6872 0.1018
-2.750 -0.0714 0.03177 0.01999 -0.0360 0.6836 0.1241
-2.500 -0.0495 0.03075 0.01952 -0.0363 0.6799 0.2018
-2.250 -0.0407 0.02878 0.01969 -0.0327 0.6770 0.6314
-2.000 0.1195 0.02927 0.02010 -0.0495 0.6753 0.9947
-1.500 0.1705 0.02975 0.02001 -0.0518 0.6687 1.0000
-1.250 0.1915 0.03021 0.02026 -0.0524 0.6647 1.0000
-1.000 0.2110 0.03058 0.02043 -0.0521 0.6614 1.0000
-0.750 0.2299 0.03090 0.02052 -0.0512 0.6586 1.0000
-0.500 0.2499 0.03152 0.02098 -0.0514 0.6547 1.0000
-0.250 0.2693 0.03224 0.02156 -0.0517 0.6501 1.0000
0.000 0.2882 0.03276 0.02192 -0.0511 0.6465 1.0000
0.250 0.3074 0.03316 0.02215 -0.0499 0.6437 1.0000
0.500 0.3249 0.03407 0.02296 -0.0501 0.6388 1.0000
0.750 0.3420 0.03488 0.02367 -0.0497 0.6340 1.0000
1.000 0.3610 0.03541 0.02408 -0.0487 0.6306 1.0000
1.250 0.3816 0.03577 0.02431 -0.0474 0.6279 1.0000
1.500 0.3931 0.03718 0.02569 -0.0477 0.6208 1.0000
1.750 0.4115 0.03780 0.02622 -0.0467 0.6166 1.0000
2.000 0.4329 0.03819 0.02651 -0.0455 0.6137 1.0000
2.500 0.4612 0.04028 0.02852 -0.0444 0.6018 1.0000
2.750 0.4843 0.04064 0.02882 -0.0433 0.5989 1.0000
3.000 0.4910 0.04226 0.03044 -0.0430 0.5903 1.0000
3.250 0.5127 0.04278 0.03094 -0.0422 0.5863 1.0000
3.500 0.5251 0.04400 0.03214 -0.0416 0.5796 1.0000
3.750 0.5420 0.04489 0.03303 -0.0410 0.5737 1.0000
4.000 0.5670 0.04525 0.03337 -0.0402 0.5703 1.0000
4.500 0.5957 0.04747 0.03565 -0.0391 0.5570 1.0000
4.750 0.6032 0.04902 0.03723 -0.0386 0.5485 1.0000
5.000 0.6247 0.04967 0.03791 -0.0380 0.5435 1.0000
5.500 0.6531 0.05190 0.04022 -0.0368 0.5299 1.0000
5.750 0.6793 0.05227 0.04068 -0.0363 0.5262 1.0000
6.000 0.6794 0.05415 0.04260 -0.0353 0.5160 1.0000
6.500 0.7063 0.05646 0.04503 -0.0339 0.5020 1.0000
6.750 0.7308 0.05691 0.04562 -0.0334 0.4975 1.0000
7.000 0.7341 0.05879 0.04756 -0.0327 0.4878 1.0000
7.500 0.7624 0.06112 0.05008 -0.0315 0.4733 1.0000
8.000 0.7910 0.06345 0.05263 -0.0304 0.4587 1.0000
8.250 0.7953 0.06547 0.05478 -0.0300 0.4491 1.0000
8.500 0.8202 0.06572 0.05519 -0.0294 0.4439 1.0000
8.750 0.8220 0.06802 0.05759 -0.0290 0.4335 1.0000
9.000 0.8500 0.06790 0.05765 -0.0282 0.4291 1.0000
9.250 0.8494 0.07050 0.06037 -0.0280 0.4180 1.0000
9.750 0.8780 0.07283 0.06305 -0.0269 0.4025 1.0000
10.000 0.8808 0.07521 0.06556 -0.0267 0.3921 1.0000
10.250 0.9086 0.07482 0.06541 -0.0257 0.3870 1.0000
10.500 0.9083 0.07757 0.06829 -0.0255 0.3756 1.0000
10.750 0.9152 0.07951 0.07040 -0.0252 0.3658 1.0000
11.000 0.9416 0.07893 0.07012 -0.0240 0.3591 1.0000
11.250 0.9455 0.08101 0.07236 -0.0236 0.3471 1.0000
11.500 0.9613 0.08085 0.07242 -0.0223 0.3339 1.0000
11.750 0.9950 0.07682 0.06868 -0.0195 0.3178 1.0000
12.250 1.0255 0.07568 0.06800 -0.0168 0.2803 1.0000
12.500 1.0407 0.07529 0.06776 -0.0155 0.2556 1.0000
12.750 1.0455 0.07680 0.06934 -0.0150 0.2249 1.0000
13.000 1.0505 0.07809 0.07039 -0.0141 0.1822 1.0000
13.250 1.0462 0.08106 0.07293 -0.0139 0.1459 1.0000
13.500 1.0376 0.08510 0.07665 -0.0142 0.1219 1.0000
13.750 1.0302 0.08922 0.08055 -0.0146 0.1053 1.0000
14.000 1.0244 0.09325 0.08442 -0.0151 0.0927 1.0000
14.250 1.0199 0.09708 0.08812 -0.0156 0.0828 1.0000
14.500 1.0191 0.10057 0.09164 -0.0159 0.0739 1.0000
14.750 1.0191 0.10389 0.09494 -0.0162 0.0670 1.0000
15.000 1.0208 0.10697 0.09809 -0.0164 0.0610 1.0000
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Polar data table (+)
Polar graphs
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