DSMA-523A AIRFOIL (dsma523a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: DSMA-523A AIRFOIL (dsma523a-il) Reynolds number: 100,000 Max Cl/Cd: 25.7 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dsma523a-il-100000-n5.txt Download as CSV file: xf-dsma523a-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DSMA-523A AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6691 0.10297 0.09668 -0.0333 1.0000 0.0464
-11.750 -0.7119 0.08808 0.08170 -0.0425 1.0000 0.0459
-11.500 -0.7571 0.07707 0.07053 -0.0494 1.0000 0.0455
-11.250 -0.7929 0.07006 0.06335 -0.0522 1.0000 0.0453
-11.000 -0.8230 0.06496 0.05806 -0.0528 1.0000 0.0452
-10.750 -0.8497 0.06105 0.05398 -0.0516 1.0000 0.0451
-10.500 -0.8747 0.05792 0.05069 -0.0492 1.0000 0.0451
-10.250 -0.8903 0.05429 0.04681 -0.0485 1.0000 0.0453
-10.000 -0.8984 0.05076 0.04295 -0.0481 1.0000 0.0456
-9.750 -0.9002 0.04747 0.03926 -0.0476 1.0000 0.0460
-9.500 -0.8964 0.04436 0.03569 -0.0472 1.0000 0.0465
-9.250 -0.8818 0.04259 0.03386 -0.0466 1.0000 0.0472
-9.000 -0.8660 0.04102 0.03221 -0.0460 1.0000 0.0481
-8.750 -0.8502 0.03925 0.03026 -0.0456 1.0000 0.0493
-8.500 -0.8333 0.03732 0.02800 -0.0454 1.0000 0.0507
-8.250 -0.8145 0.03539 0.02563 -0.0454 1.0000 0.0520
-8.000 -0.7942 0.03382 0.02395 -0.0448 1.0000 0.0529
-7.750 -0.7734 0.03248 0.02258 -0.0441 1.0000 0.0540
-7.500 -0.7519 0.03120 0.02120 -0.0435 1.0000 0.0554
-7.250 -0.7295 0.03002 0.01980 -0.0431 1.0000 0.0574
-7.000 -0.7074 0.02887 0.01855 -0.0424 1.0000 0.0593
-6.750 -0.6856 0.02783 0.01755 -0.0416 1.0000 0.0614
-6.500 -0.6631 0.02688 0.01654 -0.0409 1.0000 0.0635
-6.250 -0.6405 0.02596 0.01557 -0.0400 1.0000 0.0654
-6.000 -0.6184 0.02503 0.01478 -0.0393 1.0000 0.0679
-5.750 -0.5948 0.02425 0.01399 -0.0389 1.0000 0.0710
-5.500 -0.5707 0.02342 0.01326 -0.0387 1.0000 0.0739
-5.250 -0.5453 0.02272 0.01262 -0.0387 1.0000 0.0770
-5.000 -0.5189 0.02207 0.01202 -0.0390 1.0000 0.0810
-4.750 -0.4919 0.02154 0.01154 -0.0394 1.0000 0.0859
-4.500 -0.4644 0.02104 0.01110 -0.0398 1.0000 0.0912
-4.250 -0.4367 0.02063 0.01072 -0.0401 1.0000 0.0988
-4.000 -0.4085 0.02019 0.01036 -0.0406 1.0000 0.1089
-3.750 -0.3801 0.01977 0.01008 -0.0411 1.0000 0.1246
-3.500 -0.3511 0.01930 0.00986 -0.0418 1.0000 0.1552
-3.250 -0.3191 0.01873 0.00963 -0.0434 1.0000 0.2111
-3.000 -0.2797 0.01786 0.00935 -0.0471 1.0000 0.3133
-2.750 -0.2523 0.01750 0.01001 -0.0470 1.0000 0.4713
-2.500 -0.2633 0.01900 0.01200 -0.0357 1.0000 0.5293
-2.250 -0.2476 0.01975 0.01281 -0.0321 1.0000 0.5862
-2.000 -0.2058 0.01967 0.01257 -0.0362 1.0000 0.6226
-1.750 -0.1678 0.01976 0.01253 -0.0391 1.0000 0.6456
-1.250 -0.1204 0.02071 0.01344 -0.0368 1.0000 0.6752
-1.000 -0.1039 0.02130 0.01407 -0.0338 1.0000 0.6882
-0.750 -0.0872 0.02187 0.01468 -0.0308 1.0000 0.7027
-0.500 -0.0663 0.02235 0.01518 -0.0291 1.0000 0.7173
-0.250 -0.0539 0.02263 0.01552 -0.0253 1.0000 0.7236
0.000 -0.0283 0.02275 0.01566 -0.0251 1.0000 0.7294
0.250 0.0153 0.02308 0.01601 -0.0283 0.9938 0.7369
0.500 0.0621 0.02339 0.01638 -0.0309 0.9790 0.7434
0.750 0.1172 0.02341 0.01644 -0.0358 0.9628 0.7512
1.000 0.1529 0.02287 0.01598 -0.0366 0.9412 0.7560
1.250 0.2068 0.02188 0.01505 -0.0395 0.9137 0.7601
1.500 0.2316 0.02128 0.01453 -0.0379 0.8775 0.7635
1.750 0.2574 0.02079 0.01410 -0.0370 0.8310 0.7656
2.000 0.3702 0.02100 0.01228 -0.0501 0.3908 0.7647
2.250 0.3978 0.02196 0.01246 -0.0507 0.2415 0.7667
2.500 0.4263 0.02269 0.01268 -0.0514 0.1594 0.7686
2.750 0.4557 0.02319 0.01296 -0.0522 0.1285 0.7699
3.000 0.4859 0.02366 0.01331 -0.0532 0.1140 0.7715
3.500 0.5377 0.02447 0.01403 -0.0527 0.0971 0.7738
3.750 0.5636 0.02494 0.01448 -0.0525 0.0919 0.7746
4.000 0.5897 0.02555 0.01504 -0.0524 0.0874 0.7754
4.250 0.6171 0.02604 0.01557 -0.0525 0.0827 0.7761
4.500 0.6443 0.02663 0.01614 -0.0526 0.0789 0.7769
4.750 0.6718 0.02755 0.01695 -0.0528 0.0761 0.7778
5.000 0.7003 0.02821 0.01773 -0.0530 0.0733 0.7790
5.250 0.7285 0.02891 0.01852 -0.0532 0.0700 0.7803
5.500 0.7567 0.02967 0.01928 -0.0535 0.0673 0.7814
5.750 0.7860 0.03078 0.02032 -0.0542 0.0654 0.7822
6.000 0.8152 0.03186 0.02159 -0.0546 0.0635 0.7829
6.250 0.8435 0.03290 0.02284 -0.0549 0.0610 0.7837
6.500 0.8709 0.03389 0.02395 -0.0551 0.0588 0.7845
6.750 0.8978 0.03497 0.02510 -0.0554 0.0572 0.7852
7.000 0.9247 0.03639 0.02655 -0.0558 0.0561 0.7860
7.250 0.9490 0.03823 0.02876 -0.0555 0.0550 0.7868
7.500 0.9713 0.04025 0.03121 -0.0549 0.0536 0.7880
7.750 0.9921 0.04222 0.03353 -0.0543 0.0520 0.7891
8.000 1.0129 0.04396 0.03551 -0.0539 0.0506 0.7902
8.250 1.0324 0.04546 0.03718 -0.0532 0.0495 0.7909
8.500 1.0497 0.04722 0.03910 -0.0522 0.0488 0.7915
8.750 1.0655 0.04927 0.04132 -0.0512 0.0482 0.7921
9.000 1.0721 0.05244 0.04493 -0.0491 0.0477 0.7927
9.250 1.0700 0.05644 0.04949 -0.0463 0.0473 0.7933
9.500 1.0622 0.06078 0.05433 -0.0434 0.0470 0.7939
9.750 1.0479 0.06537 0.05936 -0.0405 0.0467 0.7945
10.000 1.0250 0.06991 0.06426 -0.0373 0.0465 0.7951
10.250 0.9970 0.07530 0.06996 -0.0356 0.0465 0.7956
10.500 0.9623 0.08224 0.07718 -0.0364 0.0466 0.7961
10.750 0.9230 0.09218 0.08737 -0.0424 0.0469 0.7964
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