AH21 9% version (Andrew Hollom) (ah21-9-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH21 9% version (Andrew Hollom) (ah21-9-il) Reynolds number: 100,000 Max Cl/Cd: 48.95 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah21-9-il-100000-n5.txt Download as CSV file: xf-ah21-9-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH21 9% version (Andrew Hollom)
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 -0.3994 0.10839 0.10337 -0.0249 1.0000 0.0471
-10.000 -0.4029 0.10496 0.09997 -0.0262 1.0000 0.0500
-9.000 -0.4919 0.09877 0.09365 -0.0247 1.0000 0.0459
-8.500 -0.5011 0.09039 0.08539 -0.0283 1.0000 0.0378
-8.250 -0.5071 0.08682 0.08190 -0.0292 1.0000 0.0378
-8.000 -0.5118 0.08358 0.07873 -0.0286 1.0000 0.0361
-7.750 -0.5267 0.07554 0.07072 -0.0357 1.0000 0.0276
-7.500 -0.5295 0.07083 0.06594 -0.0380 1.0000 0.0279
-7.250 -0.5314 0.06672 0.06180 -0.0381 1.0000 0.0276
-7.000 -0.5315 0.06230 0.05727 -0.0386 1.0000 0.0276
-6.750 -0.5298 0.05807 0.05294 -0.0385 1.0000 0.0273
-6.500 -0.5257 0.05377 0.04847 -0.0384 1.0000 0.0268
-6.250 -0.5189 0.04943 0.04391 -0.0383 1.0000 0.0264
-6.000 -0.5091 0.04510 0.03927 -0.0380 1.0000 0.0261
-5.750 -0.4964 0.04089 0.03463 -0.0376 1.0000 0.0259
-5.500 -0.4808 0.03697 0.03026 -0.0370 1.0000 0.0259
-5.250 -0.4626 0.03341 0.02617 -0.0363 1.0000 0.0262
-5.000 -0.4411 0.03111 0.02321 -0.0353 1.0000 0.0281
-4.750 -0.4214 0.02797 0.01973 -0.0350 1.0000 0.0299
-4.500 -0.3987 0.02579 0.01717 -0.0342 1.0000 0.0305
-4.250 -0.3751 0.02395 0.01499 -0.0335 1.0000 0.0313
-4.000 -0.3512 0.02240 0.01318 -0.0327 1.0000 0.0324
-3.750 -0.3270 0.02110 0.01166 -0.0319 1.0000 0.0339
-3.500 -0.3032 0.02029 0.01062 -0.0311 1.0000 0.0376
-3.250 -0.2792 0.01945 0.00961 -0.0303 1.0000 0.0396
-3.000 -0.2557 0.01835 0.00848 -0.0295 1.0000 0.0410
-2.750 -0.2323 0.01756 0.00765 -0.0289 1.0000 0.0434
-2.500 -0.2086 0.01700 0.00700 -0.0282 1.0000 0.0469
-2.250 -0.1847 0.01656 0.00641 -0.0274 1.0000 0.0526
-2.000 -0.1607 0.01595 0.00585 -0.0269 1.0000 0.0712
-1.750 -0.1368 0.01482 0.00556 -0.0269 1.0000 0.2441
-1.500 -0.1196 0.01324 0.00578 -0.0249 1.0000 0.6626
-1.250 -0.0914 0.01260 0.00579 -0.0234 1.0000 1.0000
-1.000 -0.0631 0.01274 0.00570 -0.0239 0.9981 1.0000
-0.750 -0.0273 0.01299 0.00570 -0.0260 0.9938 1.0000
-0.500 0.0071 0.01316 0.00571 -0.0277 0.9887 1.0000
-0.250 0.0434 0.01341 0.00581 -0.0298 0.9841 1.0000
0.000 0.0775 0.01359 0.00586 -0.0315 0.9785 1.0000
0.250 0.1131 0.01378 0.00597 -0.0334 0.9727 1.0000
0.500 0.1488 0.01397 0.00609 -0.0353 0.9669 1.0000
0.750 0.1836 0.01411 0.00620 -0.0370 0.9598 1.0000
1.000 0.2193 0.01423 0.00631 -0.0388 0.9528 1.0000
1.250 0.2560 0.01432 0.00641 -0.0407 0.9449 1.0000
1.500 0.2901 0.01436 0.00648 -0.0421 0.9353 1.0000
1.750 0.3281 0.01434 0.00653 -0.0440 0.9255 1.0000
2.000 0.3689 0.01422 0.00649 -0.0464 0.9149 1.0000
2.250 0.4056 0.01400 0.00637 -0.0477 0.9003 1.0000
2.500 0.4405 0.01369 0.00620 -0.0485 0.8820 1.0000
2.750 0.4804 0.01328 0.00591 -0.0500 0.8612 1.0000
3.000 0.5127 0.01299 0.00574 -0.0500 0.8298 1.0000
3.250 0.5532 0.01261 0.00548 -0.0514 0.7819 1.0000
3.500 0.6080 0.01242 0.00497 -0.0550 0.6539 1.0000
3.750 0.6331 0.01333 0.00504 -0.0537 0.4799 1.0000
4.000 0.6490 0.01449 0.00547 -0.0515 0.3370 1.0000
4.250 0.6664 0.01564 0.00608 -0.0499 0.2232 1.0000
4.500 0.6857 0.01667 0.00671 -0.0486 0.1496 1.0000
4.750 0.7062 0.01761 0.00743 -0.0474 0.1089 1.0000
5.000 0.7269 0.01852 0.00823 -0.0463 0.0851 1.0000
5.250 0.7478 0.01942 0.00913 -0.0451 0.0702 1.0000
5.500 0.7687 0.02034 0.01005 -0.0439 0.0593 1.0000
5.750 0.7895 0.02135 0.01112 -0.0427 0.0529 1.0000
6.000 0.8102 0.02265 0.01257 -0.0414 0.0488 1.0000
6.250 0.8329 0.02394 0.01401 -0.0404 0.0449 1.0000
6.500 0.8548 0.02509 0.01520 -0.0396 0.0406 1.0000
6.750 0.8778 0.02677 0.01703 -0.0389 0.0374 1.0000
7.000 0.9020 0.02866 0.01922 -0.0381 0.0354 1.0000
7.250 0.9250 0.03086 0.02176 -0.0371 0.0336 1.0000
7.500 0.9458 0.03326 0.02453 -0.0359 0.0320 1.0000
7.750 0.9636 0.03501 0.02651 -0.0347 0.0297 1.0000
8.000 0.9775 0.03781 0.02964 -0.0332 0.0274 1.0000
8.250 0.9892 0.04103 0.03348 -0.0308 0.0265 1.0000
8.500 0.9956 0.04490 0.03795 -0.0281 0.0257 1.0000
8.750 0.9968 0.04908 0.04267 -0.0252 0.0250 1.0000
9.000 0.9942 0.05317 0.04723 -0.0223 0.0239 1.0000
9.250 0.9882 0.05712 0.05155 -0.0197 0.0230 1.0000
9.500 0.9797 0.06077 0.05548 -0.0172 0.0221 1.0000
9.750 0.9642 0.06450 0.05943 -0.0145 0.0218 1.0000
10.000 0.9434 0.06886 0.06398 -0.0126 0.0219 1.0000
10.250 0.9159 0.07495 0.07024 -0.0129 0.0227 1.0000
10.500 0.8905 0.08211 0.07752 -0.0163 0.0235 1.0000
10.750 0.8695 0.09122 0.08667 -0.0228 0.0246 1.0000
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Polar data table (+)
Polar graphs
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