AG36 (ag36-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG36 (ag36-il) Reynolds number: 200,000 Max Cl/Cd: 64.27 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag36-il-200000-n5.txt Download as CSV file: xf-ag36-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG36
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5265 0.09640 0.09285 -0.0049 1.0000 0.0165
-10.250 -0.5242 0.09250 0.08897 -0.0067 1.0000 0.0163
-10.000 -0.5229 0.08832 0.08482 -0.0089 1.0000 0.0161
-9.750 -0.5229 0.08381 0.08036 -0.0118 1.0000 0.0160
-9.500 -0.5251 0.07866 0.07526 -0.0161 1.0000 0.0161
-9.250 -0.5230 0.07206 0.06866 -0.0233 1.0000 0.0162
-9.000 -0.5179 0.06436 0.06091 -0.0309 1.0000 0.0164
-8.750 -0.5112 0.05629 0.05268 -0.0370 1.0000 0.0165
-8.500 -0.5041 0.04896 0.04512 -0.0407 1.0000 0.0165
-8.250 -0.4955 0.04260 0.03843 -0.0426 1.0000 0.0163
-8.000 -0.4849 0.03664 0.03201 -0.0434 1.0000 0.0162
-7.750 -0.4715 0.03148 0.02629 -0.0433 1.0000 0.0163
-7.500 -0.4547 0.02749 0.02169 -0.0425 1.0000 0.0165
-7.250 -0.4353 0.02460 0.01826 -0.0416 1.0000 0.0168
-7.000 -0.4150 0.02233 0.01570 -0.0408 1.0000 0.0173
-6.750 -0.3933 0.02103 0.01423 -0.0400 1.0000 0.0180
-6.500 -0.3711 0.02018 0.01322 -0.0391 1.0000 0.0193
-6.250 -0.3486 0.01911 0.01193 -0.0381 1.0000 0.0207
-6.000 -0.3230 0.01780 0.01038 -0.0376 0.9990 0.0216
-5.750 -0.2876 0.01660 0.00894 -0.0391 0.9947 0.0225
-5.500 -0.2538 0.01528 0.00755 -0.0405 0.9895 0.0240
-5.250 -0.2176 0.01460 0.00683 -0.0424 0.9843 0.0266
-5.000 -0.1830 0.01400 0.00614 -0.0437 0.9770 0.0298
-4.750 -0.1477 0.01316 0.00527 -0.0453 0.9702 0.0330
-4.500 -0.1152 0.01270 0.00475 -0.0462 0.9604 0.0383
-4.250 -0.0819 0.01218 0.00423 -0.0473 0.9510 0.0464
-4.000 -0.0483 0.01172 0.00378 -0.0484 0.9412 0.0611
-3.750 -0.0174 0.01126 0.00343 -0.0490 0.9283 0.0939
-3.500 0.0126 0.01073 0.00317 -0.0495 0.9140 0.1654
-3.250 0.0413 0.01018 0.00299 -0.0498 0.8975 0.2696
-3.000 0.0685 0.00962 0.00282 -0.0497 0.8785 0.3895
-2.750 0.0937 0.00894 0.00270 -0.0490 0.8596 0.5531
-2.500 0.1134 0.00824 0.00266 -0.0464 0.8399 0.7557
-2.250 0.1461 0.00795 0.00261 -0.0460 0.8189 0.9372
-2.000 0.1897 0.00794 0.00242 -0.0490 0.7966 1.0000
-1.750 0.2154 0.00802 0.00232 -0.0484 0.7736 1.0000
-1.500 0.2412 0.00811 0.00224 -0.0477 0.7500 1.0000
-1.250 0.2670 0.00822 0.00217 -0.0471 0.7246 1.0000
-1.000 0.2930 0.00833 0.00212 -0.0466 0.6960 1.0000
-0.750 0.3190 0.00846 0.00208 -0.0461 0.6611 1.0000
-0.500 0.3446 0.00863 0.00204 -0.0455 0.6323 1.0000
-0.250 0.3706 0.00883 0.00204 -0.0450 0.6105 1.0000
0.000 0.3969 0.00903 0.00209 -0.0446 0.5923 1.0000
0.250 0.4235 0.00922 0.00216 -0.0444 0.5761 1.0000
0.500 0.4502 0.00941 0.00227 -0.0441 0.5610 1.0000
0.750 0.4770 0.00959 0.00237 -0.0439 0.5463 1.0000
1.000 0.5039 0.00978 0.00249 -0.0437 0.5319 1.0000
1.250 0.5308 0.00996 0.00261 -0.0435 0.5172 1.0000
1.500 0.5577 0.01014 0.00276 -0.0434 0.5023 1.0000
1.750 0.5846 0.01031 0.00291 -0.0432 0.4867 1.0000
2.000 0.6115 0.01048 0.00306 -0.0431 0.4695 1.0000
2.250 0.6382 0.01066 0.00321 -0.0429 0.4504 1.0000
2.500 0.6648 0.01085 0.00339 -0.0428 0.4294 1.0000
2.750 0.6911 0.01109 0.00357 -0.0426 0.4069 1.0000
3.000 0.7173 0.01134 0.00378 -0.0424 0.3819 1.0000
3.250 0.7433 0.01164 0.00403 -0.0421 0.3565 1.0000
3.500 0.7690 0.01198 0.00430 -0.0419 0.3307 1.0000
3.750 0.7944 0.01236 0.00461 -0.0417 0.3045 1.0000
4.000 0.8197 0.01276 0.00495 -0.0414 0.2779 1.0000
4.250 0.8447 0.01320 0.00533 -0.0412 0.2500 1.0000
4.500 0.8696 0.01367 0.00574 -0.0410 0.2232 1.0000
4.750 0.8943 0.01417 0.00618 -0.0407 0.1971 1.0000
5.000 0.9185 0.01473 0.00666 -0.0404 0.1702 1.0000
5.250 0.9423 0.01534 0.00721 -0.0401 0.1437 1.0000
5.500 0.9660 0.01597 0.00777 -0.0398 0.1198 1.0000
5.750 0.9891 0.01666 0.00838 -0.0394 0.0978 1.0000
6.000 1.0121 0.01737 0.00904 -0.0391 0.0763 1.0000
6.250 1.0343 0.01818 0.00979 -0.0386 0.0570 1.0000
6.500 1.0556 0.01910 0.01068 -0.0380 0.0415 1.0000
6.750 1.0763 0.02008 0.01166 -0.0373 0.0314 1.0000
7.000 1.0971 0.02103 0.01270 -0.0365 0.0257 1.0000
7.250 1.1161 0.02217 0.01390 -0.0356 0.0219 1.0000
7.500 1.1359 0.02313 0.01499 -0.0348 0.0189 1.0000
7.750 1.1523 0.02447 0.01644 -0.0337 0.0168 1.0000
8.000 1.1694 0.02567 0.01781 -0.0326 0.0156 1.0000
8.250 1.1850 0.02698 0.01927 -0.0313 0.0146 1.0000
8.500 1.1993 0.02836 0.02079 -0.0300 0.0137 1.0000
8.750 1.2121 0.02978 0.02233 -0.0286 0.0129 1.0000
9.000 1.2202 0.03163 0.02427 -0.0268 0.0122 1.0000
9.250 1.2308 0.03317 0.02600 -0.0252 0.0116 1.0000
9.500 1.2384 0.03473 0.02778 -0.0233 0.0110 1.0000
9.750 1.2430 0.03647 0.02970 -0.0212 0.0105 1.0000
10.000 1.2456 0.03849 0.03189 -0.0194 0.0102 1.0000
10.250 1.2469 0.04072 0.03430 -0.0179 0.0099 1.0000
10.500 1.2468 0.04321 0.03697 -0.0168 0.0097 1.0000
10.750 1.2454 0.04600 0.03994 -0.0162 0.0095 1.0000
11.000 1.2425 0.04914 0.04325 -0.0161 0.0093 1.0000
11.250 1.2381 0.05266 0.04695 -0.0166 0.0092 1.0000
11.500 1.2322 0.05661 0.05108 -0.0175 0.0091 1.0000
11.750 1.2245 0.06107 0.05573 -0.0190 0.0090 1.0000
12.000 1.2154 0.06602 0.06086 -0.0211 0.0089 1.0000
12.250 1.2043 0.07147 0.06649 -0.0236 0.0089 1.0000
12.500 1.1916 0.07740 0.07260 -0.0264 0.0089 1.0000
12.750 1.1772 0.08380 0.07919 -0.0297 0.0088 1.0000
13.000 1.1613 0.09076 0.08633 -0.0334 0.0088 1.0000
13.250 1.1441 0.09834 0.09411 -0.0375 0.0089 1.0000
13.500 1.1249 0.10686 0.10282 -0.0423 0.0089 1.0000
13.750 1.1026 0.11671 0.11286 -0.0479 0.0090 1.0000
14.000 1.0723 0.12940 0.12578 -0.0550 0.0092 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG36 (ag36-il)