AH 80-136 (ah80136-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 80-136 (ah80136-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.55 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah80136-il-1000000-n5.txt Download as CSV file: xf-ah80136-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6159 0.14818 0.14550 0.0569 0.5883 0.0046
-12.000 -0.6123 0.14413 0.14144 0.0551 0.5870 0.0046
-11.000 -1.0193 0.03474 0.03106 0.0015 0.5945 0.0047
-10.750 -1.0133 0.03123 0.02721 0.0027 0.5929 0.0048
-10.500 -1.0007 0.02869 0.02439 0.0037 0.5912 0.0049
-10.250 -0.9840 0.02677 0.02224 0.0045 0.5894 0.0050
-10.000 -0.9648 0.02520 0.02047 0.0052 0.5876 0.0050
-9.750 -0.9440 0.02387 0.01896 0.0058 0.5859 0.0051
-9.500 -0.9220 0.02271 0.01762 0.0063 0.5840 0.0052
-9.250 -0.8992 0.02163 0.01640 0.0068 0.5825 0.0053
-9.000 -0.8757 0.02064 0.01526 0.0072 0.5808 0.0055
-8.750 -0.8517 0.01972 0.01420 0.0076 0.5790 0.0056
-8.500 -0.8272 0.01886 0.01320 0.0080 0.5773 0.0057
-8.250 -0.8022 0.01806 0.01227 0.0083 0.5756 0.0059
-8.000 -0.7768 0.01733 0.01141 0.0086 0.5740 0.0060
-7.750 -0.7511 0.01665 0.01060 0.0088 0.5724 0.0062
-7.500 -0.7250 0.01603 0.00987 0.0090 0.5708 0.0063
-7.250 -0.6986 0.01546 0.00920 0.0092 0.5692 0.0065
-7.000 -0.6719 0.01493 0.00857 0.0094 0.5678 0.0066
-6.750 -0.6450 0.01445 0.00801 0.0095 0.5662 0.0067
-6.500 -0.6186 0.01381 0.00729 0.0097 0.5646 0.0069
-6.250 -0.5918 0.01328 0.00668 0.0098 0.5631 0.0072
-6.000 -0.5644 0.01288 0.00623 0.0099 0.5616 0.0075
-5.750 -0.5367 0.01253 0.00583 0.0099 0.5601 0.0078
-5.500 -0.5089 0.01222 0.00547 0.0099 0.5585 0.0082
-5.250 -0.4809 0.01191 0.00511 0.0098 0.5569 0.0086
-5.000 -0.4529 0.01163 0.00477 0.0098 0.5551 0.0090
-4.750 -0.4246 0.01138 0.00449 0.0097 0.5539 0.0095
-4.500 -0.3966 0.01105 0.00414 0.0096 0.5526 0.0104
-4.250 -0.3682 0.01082 0.00391 0.0095 0.5512 0.0114
-4.000 -0.3397 0.01061 0.00368 0.0094 0.5497 0.0123
-3.750 -0.3110 0.01042 0.00345 0.0093 0.5481 0.0131
-3.500 -0.2825 0.01019 0.00321 0.0091 0.5464 0.0146
-3.250 -0.2538 0.01002 0.00302 0.0089 0.5447 0.0161
-3.000 -0.2249 0.00987 0.00285 0.0087 0.5432 0.0174
-2.750 -0.1960 0.00971 0.00267 0.0085 0.5418 0.0192
-2.500 -0.1671 0.00957 0.00254 0.0083 0.5404 0.0216
-2.250 -0.1381 0.00945 0.00241 0.0080 0.5390 0.0236
-2.000 -0.1091 0.00929 0.00226 0.0078 0.5374 0.0266
-1.750 -0.0800 0.00915 0.00214 0.0076 0.5358 0.0295
-1.500 -0.0508 0.00905 0.00202 0.0073 0.5343 0.0319
-1.250 -0.0217 0.00893 0.00191 0.0070 0.5327 0.0375
-1.000 0.0075 0.00882 0.00181 0.0067 0.5309 0.0428
-0.750 0.0366 0.00869 0.00170 0.0064 0.5292 0.0581
-0.500 0.0650 0.00835 0.00160 0.0061 0.5276 0.1341
-0.250 0.0931 0.00795 0.00150 0.0058 0.5260 0.2341
0.000 0.1200 0.00728 0.00140 0.0055 0.5245 0.4049
0.250 0.1476 0.00683 0.00136 0.0053 0.5228 0.5342
0.500 0.1762 0.00663 0.00134 0.0051 0.5210 0.5915
0.750 0.2027 0.00614 0.00131 0.0052 0.5190 0.7223
1.000 0.2254 0.00566 0.00136 0.0065 0.5170 0.8763
1.250 0.2499 0.00561 0.00142 0.0076 0.5148 0.9332
1.500 0.2782 0.00563 0.00144 0.0076 0.5119 0.9477
1.750 0.3080 0.00564 0.00145 0.0072 0.5089 0.9553
2.000 0.3379 0.00567 0.00146 0.0068 0.5058 0.9627
2.250 0.3692 0.00570 0.00148 0.0060 0.5030 0.9680
2.500 0.4004 0.00575 0.00150 0.0052 0.5005 0.9734
2.750 0.4320 0.00580 0.00153 0.0043 0.4980 0.9777
3.000 0.4649 0.00584 0.00156 0.0032 0.4955 0.9807
3.250 0.4973 0.00588 0.00161 0.0021 0.4925 0.9845
3.500 0.5300 0.00593 0.00165 0.0009 0.4894 0.9883
3.750 0.5635 0.00599 0.00170 -0.0004 0.4862 0.9913
4.000 0.5963 0.00605 0.00176 -0.0017 0.4831 0.9940
4.250 0.6302 0.00610 0.00182 -0.0031 0.4797 0.9957
4.500 0.6644 0.00615 0.00188 -0.0047 0.4757 0.9970
4.750 0.6981 0.00623 0.00195 -0.0061 0.4714 0.9985
5.000 0.7316 0.00629 0.00203 -0.0075 0.4673 1.0000
5.250 0.7591 0.00636 0.00211 -0.0077 0.4616 1.0000
5.500 0.7867 0.00646 0.00219 -0.0079 0.4547 1.0000
5.750 0.8144 0.00655 0.00230 -0.0081 0.4467 1.0000
6.000 0.8421 0.00667 0.00242 -0.0083 0.4394 1.0000
6.250 0.8699 0.00682 0.00255 -0.0086 0.4289 1.0000
6.500 0.8977 0.00704 0.00273 -0.0090 0.4121 1.0000
6.750 0.9256 0.00731 0.00295 -0.0095 0.3923 1.0000
7.000 0.9534 0.00778 0.00329 -0.0101 0.3615 1.0000
7.250 0.9810 0.00826 0.00367 -0.0109 0.3338 1.0000
7.500 1.0083 0.00889 0.00416 -0.0117 0.3014 1.0000
7.750 1.0353 0.00954 0.00467 -0.0125 0.2696 1.0000
8.000 1.0604 0.01078 0.00558 -0.0138 0.2073 1.0000
8.250 1.0834 0.01227 0.00672 -0.0152 0.1459 1.0000
8.500 1.1055 0.01364 0.00786 -0.0165 0.0992 1.0000
8.750 1.1262 0.01517 0.00918 -0.0180 0.0614 1.0000
9.000 1.1489 0.01650 0.01044 -0.0198 0.0441 1.0000
9.250 1.1718 0.01792 0.01184 -0.0221 0.0344 1.0000
9.500 1.1916 0.01937 0.01327 -0.0238 0.0271 1.0000
9.750 1.2080 0.02085 0.01474 -0.0248 0.0214 1.0000
10.000 1.2202 0.02225 0.01615 -0.0249 0.0174 1.0000
10.250 1.2311 0.02376 0.01767 -0.0248 0.0140 1.0000
10.500 1.2414 0.02531 0.01922 -0.0248 0.0113 1.0000
10.750 1.2523 0.02680 0.02073 -0.0247 0.0097 1.0000
11.000 1.2617 0.02839 0.02235 -0.0245 0.0083 1.0000
11.250 1.2714 0.02994 0.02393 -0.0242 0.0073 1.0000
11.500 1.2806 0.03153 0.02556 -0.0240 0.0066 1.0000
11.750 1.2882 0.03323 0.02731 -0.0237 0.0060 1.0000
12.000 1.2948 0.03503 0.02915 -0.0234 0.0053 1.0000
12.250 1.3029 0.03671 0.03088 -0.0231 0.0050 1.0000
12.500 1.3105 0.03842 0.03263 -0.0228 0.0047 1.0000
12.750 1.3170 0.04029 0.03455 -0.0226 0.0044 1.0000
13.000 1.3237 0.04219 0.03650 -0.0224 0.0041 1.0000
13.250 1.3292 0.04427 0.03862 -0.0222 0.0038 1.0000
13.500 1.3342 0.04640 0.04081 -0.0221 0.0036 1.0000
13.750 1.3383 0.04870 0.04317 -0.0220 0.0034 1.0000
14.000 1.3445 0.05079 0.04533 -0.0219 0.0033 1.0000
14.250 1.3492 0.05307 0.04767 -0.0219 0.0032 1.0000
14.500 1.3542 0.05533 0.04999 -0.0219 0.0031 1.0000
14.750 1.3579 0.05780 0.05253 -0.0220 0.0030 1.0000
15.000 1.3617 0.06024 0.05504 -0.0221 0.0030 1.0000
15.250 1.3642 0.06290 0.05777 -0.0223 0.0029 1.0000
15.500 1.3671 0.06553 0.06046 -0.0225 0.0028 1.0000
15.750 1.3688 0.06835 0.06336 -0.0228 0.0027 1.0000
16.000 1.3702 0.07122 0.06629 -0.0231 0.0026 1.0000
16.250 1.3711 0.07419 0.06934 -0.0235 0.0026 1.0000
16.500 1.3711 0.07734 0.07256 -0.0239 0.0025 1.0000
16.750 1.3711 0.08053 0.07581 -0.0244 0.0024 1.0000
17.000 1.3693 0.08397 0.07935 -0.0251 0.0024 1.0000
17.250 1.3673 0.08748 0.08293 -0.0257 0.0023 1.0000
17.500 1.3648 0.09113 0.08667 -0.0265 0.0023 1.0000
17.750 1.3608 0.09506 0.09068 -0.0274 0.0022 1.0000
18.000 1.3559 0.09914 0.09485 -0.0285 0.0022 1.0000
18.250 1.3502 0.10339 0.09919 -0.0296 0.0022 1.0000
18.500 1.3430 0.10794 0.10384 -0.0309 0.0021 1.0000
18.750 1.3355 0.11266 0.10865 -0.0324 0.0021 1.0000
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Polar data table (+)
Polar graphs
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