ARA-D 20% AIRFOIL (arad20-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: ARA-D 20% AIRFOIL (arad20-il) Reynolds number: 500,000 Max Cl/Cd: 80.12 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad20-il-500000-n5.txt Download as CSV file: xf-arad20-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 20% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.1024 0.09477 0.09021 -0.0138 1.0000 0.0178
-17.750 -1.1247 0.08719 0.08249 -0.0178 1.0000 0.0179
-17.500 -1.1461 0.07987 0.07503 -0.0217 1.0000 0.0179
-17.250 -1.1654 0.07312 0.06813 -0.0252 1.0000 0.0180
-17.000 -1.1816 0.06693 0.06179 -0.0284 1.0000 0.0180
-16.750 -1.1958 0.06116 0.05589 -0.0313 1.0000 0.0181
-16.500 -1.2076 0.05585 0.05045 -0.0339 1.0000 0.0182
-16.250 -1.2160 0.05118 0.04567 -0.0361 1.0000 0.0183
-16.000 -1.2211 0.04712 0.04151 -0.0377 1.0000 0.0185
-15.750 -1.2230 0.04362 0.03791 -0.0389 1.0000 0.0186
-15.500 -1.2226 0.04058 0.03478 -0.0397 1.0000 0.0188
-15.250 -1.2203 0.03793 0.03204 -0.0400 1.0000 0.0190
-15.000 -1.2163 0.03561 0.02965 -0.0400 1.0000 0.0192
-14.750 -1.2111 0.03358 0.02754 -0.0395 1.0000 0.0195
-14.500 -1.2053 0.03179 0.02568 -0.0387 1.0000 0.0197
-14.250 -1.1994 0.03021 0.02402 -0.0373 1.0000 0.0200
-14.000 -1.1947 0.02883 0.02256 -0.0353 1.0000 0.0203
-13.750 -1.1878 0.02771 0.02137 -0.0330 1.0000 0.0205
-13.500 -1.1737 0.02678 0.02037 -0.0315 1.0000 0.0209
-13.250 -1.1581 0.02585 0.01941 -0.0302 1.0000 0.0213
-13.000 -1.1404 0.02500 0.01854 -0.0291 1.0000 0.0217
-12.750 -1.1205 0.02425 0.01777 -0.0282 1.0000 0.0223
-12.500 -1.0992 0.02356 0.01705 -0.0275 1.0000 0.0229
-12.250 -1.0768 0.02291 0.01636 -0.0268 1.0000 0.0235
-12.000 -1.0492 0.02238 0.01574 -0.0271 0.9291 0.0242
-11.750 -1.0323 0.02204 0.01514 -0.0248 0.8306 0.0248
-11.500 -1.0112 0.02176 0.01455 -0.0235 0.7447 0.0255
-11.250 -0.9872 0.02145 0.01397 -0.0229 0.6774 0.0263
-11.000 -0.9618 0.02111 0.01343 -0.0225 0.6327 0.0272
-10.750 -0.9359 0.02071 0.01290 -0.0223 0.6048 0.0281
-10.250 -0.8824 0.01995 0.01195 -0.0220 0.5683 0.0302
-10.000 -0.8549 0.01960 0.01151 -0.0219 0.5550 0.0313
-9.750 -0.8275 0.01922 0.01108 -0.0218 0.5433 0.0326
-9.500 -0.7994 0.01889 0.01069 -0.0218 0.5344 0.0340
-9.250 -0.7711 0.01856 0.01031 -0.0218 0.5266 0.0354
-9.000 -0.7427 0.01823 0.00994 -0.0218 0.5186 0.0370
-8.750 -0.7138 0.01795 0.00960 -0.0219 0.5117 0.0388
-8.500 -0.6850 0.01762 0.00926 -0.0220 0.5054 0.0406
-8.250 -0.6558 0.01735 0.00894 -0.0222 0.4994 0.0426
-8.000 -0.6266 0.01708 0.00863 -0.0223 0.4934 0.0446
-7.750 -0.5971 0.01680 0.00834 -0.0225 0.4884 0.0468
-7.500 -0.5674 0.01654 0.00806 -0.0227 0.4832 0.0491
-7.250 -0.5377 0.01629 0.00779 -0.0229 0.4782 0.0520
-7.000 -0.5079 0.01606 0.00753 -0.0232 0.4731 0.0551
-6.500 -0.4478 0.01559 0.00706 -0.0237 0.4643 0.0634
-6.250 -0.4176 0.01536 0.00683 -0.0240 0.4599 0.0684
-6.000 -0.3873 0.01515 0.00662 -0.0243 0.4553 0.0740
-5.750 -0.3570 0.01496 0.00642 -0.0247 0.4505 0.0803
-5.500 -0.3265 0.01476 0.00623 -0.0250 0.4467 0.0875
-5.250 -0.2959 0.01455 0.00605 -0.0254 0.4429 0.0958
-5.000 -0.2653 0.01435 0.00588 -0.0258 0.4384 0.1053
-4.750 -0.2346 0.01417 0.00572 -0.0262 0.4340 0.1161
-4.500 -0.2039 0.01400 0.00557 -0.0266 0.4298 0.1284
-4.250 -0.1731 0.01383 0.00543 -0.0271 0.4260 0.1425
-3.750 -0.1114 0.01345 0.00518 -0.0280 0.4179 0.1765
-3.500 -0.0805 0.01328 0.00507 -0.0285 0.4137 0.1971
-3.250 -0.0496 0.01314 0.00496 -0.0290 0.4093 0.2193
-3.000 -0.0186 0.01296 0.00487 -0.0295 0.4055 0.2441
-2.750 0.0125 0.01278 0.00479 -0.0301 0.4016 0.2724
-2.500 0.0435 0.01259 0.00472 -0.0306 0.3972 0.3060
-2.250 0.0746 0.01244 0.00466 -0.0312 0.3926 0.3407
-2.000 0.1056 0.01233 0.00461 -0.0318 0.3882 0.3723
-1.750 0.1368 0.01220 0.00458 -0.0323 0.3846 0.4021
-1.500 0.1680 0.01209 0.00456 -0.0328 0.3800 0.4327
-1.250 0.1991 0.01201 0.00455 -0.0334 0.3751 0.4620
-1.000 0.2301 0.01197 0.00455 -0.0339 0.3708 0.4898
-0.750 0.2613 0.01190 0.00457 -0.0344 0.3669 0.5195
-0.500 0.2924 0.01184 0.00459 -0.0349 0.3622 0.5483
-0.250 0.3234 0.01183 0.00462 -0.0354 0.3571 0.5733
0.000 0.3543 0.01184 0.00465 -0.0359 0.3524 0.5971
0.250 0.3853 0.01183 0.00470 -0.0364 0.3485 0.6201
0.500 0.4163 0.01184 0.00476 -0.0368 0.3436 0.6417
0.750 0.4471 0.01187 0.00482 -0.0373 0.3384 0.6622
1.000 0.4777 0.01193 0.00489 -0.0377 0.3337 0.6817
1.250 0.5084 0.01196 0.00497 -0.0381 0.3297 0.7000
1.500 0.5391 0.01202 0.00504 -0.0386 0.3248 0.7175
1.750 0.5695 0.01210 0.00513 -0.0389 0.3196 0.7349
2.000 0.5998 0.01218 0.00523 -0.0393 0.3152 0.7511
2.250 0.6302 0.01225 0.00534 -0.0397 0.3110 0.7664
2.500 0.6604 0.01235 0.00544 -0.0400 0.3063 0.7822
2.750 0.6901 0.01247 0.00556 -0.0403 0.3014 0.7967
3.000 0.7201 0.01257 0.00568 -0.0406 0.2973 0.8108
3.250 0.7498 0.01266 0.00580 -0.0409 0.2931 0.8252
3.500 0.7791 0.01278 0.00594 -0.0411 0.2887 0.8386
3.750 0.8083 0.01295 0.00608 -0.0414 0.2843 0.8524
4.000 0.8371 0.01304 0.00622 -0.0414 0.2805 0.8662
4.250 0.8656 0.01316 0.00636 -0.0415 0.2763 0.8797
4.750 0.9211 0.01347 0.00666 -0.0413 0.2683 0.9082
5.000 0.9482 0.01357 0.00679 -0.0410 0.2650 0.9232
5.250 0.9749 0.01367 0.00691 -0.0407 0.2610 0.9396
5.500 1.0019 0.01379 0.00702 -0.0405 0.2572 0.9593
5.750 1.0319 0.01393 0.00714 -0.0411 0.2535 0.9860
6.000 1.0624 0.01408 0.00729 -0.0418 0.2503 1.0000
6.250 1.0924 0.01430 0.00750 -0.0424 0.2466 1.0000
6.500 1.1220 0.01456 0.00773 -0.0429 0.2428 1.0000
6.750 1.1510 0.01485 0.00799 -0.0435 0.2394 1.0000
7.000 1.1802 0.01512 0.00824 -0.0440 0.2364 1.0000
7.250 1.2094 0.01535 0.00849 -0.0445 0.2332 1.0000
7.500 1.2381 0.01563 0.00875 -0.0449 0.2297 1.0000
7.750 1.2663 0.01595 0.00905 -0.0453 0.2264 1.0000
8.000 1.2939 0.01630 0.00937 -0.0456 0.2234 1.0000
8.250 1.3222 0.01655 0.00966 -0.0460 0.2207 1.0000
8.500 1.3500 0.01685 0.00996 -0.0463 0.2176 1.0000
8.750 1.3771 0.01719 0.01030 -0.0465 0.2145 1.0000
9.000 1.4034 0.01758 0.01067 -0.0467 0.2116 1.0000
9.250 1.4295 0.01795 0.01105 -0.0468 0.2090 1.0000
9.500 1.4560 0.01827 0.01140 -0.0469 0.2064 1.0000
9.750 1.4817 0.01864 0.01179 -0.0470 0.2035 1.0000
10.000 1.5065 0.01905 0.01221 -0.0469 0.2008 1.0000
10.250 1.5299 0.01953 0.01269 -0.0466 0.1981 1.0000
10.500 1.5532 0.02000 0.01317 -0.0464 0.1957 1.0000
10.750 1.5768 0.02040 0.01361 -0.0461 0.1933 1.0000
11.000 1.5991 0.02087 0.01412 -0.0457 0.1908 1.0000
11.250 1.6197 0.02141 0.01468 -0.0451 0.1883 1.0000
11.500 1.6378 0.02206 0.01533 -0.0442 0.1857 1.0000
11.750 1.6541 0.02276 0.01606 -0.0430 0.1835 1.0000
12.000 1.6712 0.02337 0.01673 -0.0419 0.1815 1.0000
12.250 1.6812 0.02417 0.01759 -0.0397 0.1795 1.0000
12.500 1.6892 0.02520 0.01867 -0.0376 0.1773 1.0000
12.750 1.6962 0.02647 0.02000 -0.0359 0.1752 1.0000
13.000 1.7013 0.02807 0.02165 -0.0345 0.1731 1.0000
13.250 1.7065 0.02989 0.02353 -0.0336 0.1713 1.0000
13.500 1.7150 0.03163 0.02536 -0.0333 0.1696 1.0000
13.750 1.7212 0.03376 0.02757 -0.0332 0.1675 1.0000
14.000 1.7242 0.03636 0.03025 -0.0334 0.1654 1.0000
14.250 1.7237 0.03949 0.03346 -0.0339 0.1633 1.0000
14.500 1.7192 0.04317 0.03720 -0.0346 0.1614 1.0000
14.750 1.7142 0.04686 0.04098 -0.0352 0.1597 1.0000
15.000 1.7124 0.05014 0.04436 -0.0357 0.1580 1.0000
15.250 1.7071 0.05379 0.04810 -0.0363 0.1561 1.0000
15.500 1.6982 0.05780 0.05220 -0.0368 0.1541 1.0000
15.750 1.6860 0.06214 0.05660 -0.0374 0.1522 1.0000
16.000 1.6719 0.06670 0.06123 -0.0380 0.1503 1.0000
16.250 1.6615 0.07097 0.06557 -0.0387 0.1486 1.0000
16.500 1.6572 0.07459 0.06928 -0.0394 0.1470 1.0000
16.750 1.6513 0.07848 0.07325 -0.0402 0.1451 1.0000
17.000 1.6433 0.08270 0.07754 -0.0412 0.1431 1.0000
17.250 1.6348 0.08697 0.08185 -0.0422 0.1410 1.0000
17.500 1.6239 0.09162 0.08654 -0.0434 0.1391 1.0000
|
Polar data table (+)
Polar graphs
<< Back to ARA-D 20% AIRFOIL (arad20-il)