I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 571 (isa571-il) Reynolds number: 200,000 Max Cl/Cd: 69.65 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa571-il-200000.txt Download as CSV file: xf-isa571-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 571
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4183 0.10682 0.10329 -0.0230 1.0000 0.0347
-9.000 -0.4217 0.10435 0.10088 -0.0240 1.0000 0.0347
-8.750 -0.4238 0.10160 0.09819 -0.0252 1.0000 0.0348
-8.500 -0.4234 0.09534 0.09196 -0.0228 1.0000 0.0355
-8.250 -0.4163 0.09171 0.08835 -0.0205 1.0000 0.0361
-8.000 -0.4139 0.08880 0.08545 -0.0196 1.0000 0.0367
-7.750 -0.4118 0.08589 0.08258 -0.0197 1.0000 0.0373
-7.500 -0.4098 0.08294 0.07967 -0.0203 1.0000 0.0380
-7.250 -0.4069 0.07988 0.07663 -0.0214 1.0000 0.0388
-7.000 -0.4027 0.07666 0.07344 -0.0228 1.0000 0.0397
-6.750 -0.3964 0.07328 0.07005 -0.0247 1.0000 0.0408
-6.500 -0.3874 0.06965 0.06641 -0.0272 1.0000 0.0423
-6.250 -0.3643 0.06548 0.06207 -0.0346 1.0000 0.0451
-6.000 -0.3436 0.06180 0.05816 -0.0382 1.0000 0.0456
-5.750 -0.3265 0.05807 0.05424 -0.0395 1.0000 0.0458
-5.500 -0.3214 0.05158 0.04783 -0.0398 1.0000 0.0470
-5.250 -0.3098 0.04914 0.04544 -0.0387 1.0000 0.0486
-5.000 -0.2934 0.04679 0.04304 -0.0386 1.0000 0.0520
-4.750 -0.2564 0.04440 0.03995 -0.0414 1.0000 0.0581
-4.500 -0.2413 0.03866 0.03426 -0.0425 1.0000 0.0600
-4.250 -0.2226 0.03648 0.03207 -0.0423 1.0000 0.0624
-4.000 -0.1936 0.03359 0.02869 -0.0434 1.0000 0.0721
-3.750 -0.1740 0.03172 0.02691 -0.0431 1.0000 0.0760
-3.500 -0.1303 0.02504 0.01914 -0.0451 1.0000 0.0600
-3.250 -0.0958 0.02168 0.01532 -0.0459 1.0000 0.0551
-3.000 -0.0548 0.01928 0.01238 -0.0484 0.9981 0.0612
-2.750 -0.0104 0.01807 0.01093 -0.0516 0.9946 0.0676
-2.500 0.0318 0.01680 0.00941 -0.0544 0.9902 0.0736
-2.250 0.0760 0.01629 0.00879 -0.0576 0.9851 0.0807
-2.000 0.1180 0.01540 0.00779 -0.0603 0.9792 0.0844
-1.750 0.1618 0.01479 0.00722 -0.0636 0.9729 0.0906
-1.500 0.2023 0.01420 0.00658 -0.0659 0.9650 0.0951
-1.250 0.2458 0.01346 0.00594 -0.0690 0.9587 0.1015
-1.000 0.2846 0.01287 0.00542 -0.0711 0.9489 0.1128
-0.750 0.3278 0.01207 0.00475 -0.0740 0.9408 0.1386
-0.250 0.3993 0.00901 0.00401 -0.0762 0.9161 1.0000
0.000 0.4330 0.00876 0.00365 -0.0767 0.8920 1.0000
0.250 0.4699 0.00852 0.00327 -0.0779 0.8613 1.0000
0.500 0.5062 0.00837 0.00293 -0.0789 0.8160 1.0000
0.750 0.5367 0.00847 0.00271 -0.0787 0.7553 1.0000
1.000 0.5620 0.00881 0.00267 -0.0777 0.6951 1.0000
1.250 0.5857 0.00923 0.00273 -0.0765 0.6422 1.0000
1.500 0.6093 0.00964 0.00285 -0.0755 0.5941 1.0000
1.750 0.6331 0.01003 0.00299 -0.0746 0.5512 1.0000
2.000 0.6575 0.01039 0.00313 -0.0739 0.5162 1.0000
2.250 0.6825 0.01073 0.00330 -0.0733 0.4892 1.0000
2.500 0.7076 0.01108 0.00348 -0.0728 0.4673 1.0000
2.750 0.7331 0.01141 0.00371 -0.0724 0.4480 1.0000
3.000 0.7587 0.01173 0.00393 -0.0720 0.4319 1.0000
3.250 0.7846 0.01204 0.00419 -0.0716 0.4186 1.0000
3.500 0.8106 0.01237 0.00446 -0.0713 0.4068 1.0000
3.750 0.8365 0.01270 0.00476 -0.0710 0.3957 1.0000
4.000 0.8624 0.01301 0.00505 -0.0707 0.3838 1.0000
4.250 0.8883 0.01329 0.00536 -0.0704 0.3717 1.0000
4.500 0.9140 0.01360 0.00569 -0.0701 0.3600 1.0000
4.750 0.9395 0.01391 0.00604 -0.0697 0.3475 1.0000
5.000 0.9647 0.01422 0.00637 -0.0693 0.3344 1.0000
5.250 0.9898 0.01454 0.00672 -0.0688 0.3209 1.0000
5.500 1.0144 0.01481 0.00704 -0.0683 0.3042 1.0000
5.750 1.0385 0.01505 0.00731 -0.0677 0.2839 1.0000
6.000 1.0627 0.01530 0.00760 -0.0672 0.2627 1.0000
6.250 1.0865 0.01560 0.00789 -0.0666 0.2398 1.0000
6.500 1.1102 0.01597 0.00825 -0.0661 0.2150 1.0000
6.750 1.1327 0.01650 0.00871 -0.0654 0.1892 1.0000
7.000 1.1544 0.01717 0.00932 -0.0646 0.1633 1.0000
7.250 1.1742 0.01813 0.00998 -0.0636 0.1015 1.0000
7.500 1.1875 0.02002 0.01136 -0.0616 0.0430 1.0000
7.750 1.2045 0.02140 0.01274 -0.0599 0.0346 1.0000
8.000 1.2221 0.02254 0.01407 -0.0583 0.0311 1.0000
8.250 1.2360 0.02400 0.01567 -0.0563 0.0281 1.0000
8.500 1.2448 0.02587 0.01771 -0.0536 0.0265 1.0000
8.750 1.2562 0.02748 0.01944 -0.0512 0.0258 1.0000
9.000 1.2683 0.02902 0.02112 -0.0489 0.0252 1.0000
9.250 1.2799 0.03072 0.02296 -0.0466 0.0246 1.0000
9.500 1.2916 0.03254 0.02492 -0.0444 0.0241 1.0000
9.750 1.3031 0.03435 0.02687 -0.0424 0.0232 1.0000
10.000 1.3130 0.03617 0.02882 -0.0402 0.0221 1.0000
10.250 1.3216 0.03821 0.03100 -0.0379 0.0214 1.0000
10.500 1.3299 0.04056 0.03357 -0.0357 0.0212 1.0000
10.750 1.3359 0.04310 0.03634 -0.0333 0.0210 1.0000
11.000 1.3387 0.04584 0.03935 -0.0308 0.0211 1.0000
11.250 1.3376 0.04883 0.04263 -0.0281 0.0212 1.0000
11.500 1.3299 0.05212 0.04625 -0.0254 0.0215 1.0000
11.750 1.3188 0.05583 0.05028 -0.0233 0.0219 1.0000
12.000 1.3043 0.05999 0.05476 -0.0219 0.0222 1.0000
12.250 1.2875 0.06469 0.05975 -0.0216 0.0226 1.0000
12.500 1.2692 0.06997 0.06530 -0.0226 0.0229 1.0000
12.750 1.2498 0.07594 0.07151 -0.0248 0.0232 1.0000
13.000 1.2295 0.08257 0.07837 -0.0281 0.0234 1.0000
13.250 1.2085 0.08988 0.08588 -0.0323 0.0237 1.0000
13.500 1.1868 0.09784 0.09402 -0.0373 0.0239 1.0000
13.750 1.1644 0.10651 0.10286 -0.0429 0.0240 1.0000
14.000 1.1408 0.11600 0.11250 -0.0492 0.0242 1.0000
14.250 1.1165 0.12631 0.12294 -0.0560 0.0244 1.0000
14.500 1.0898 0.13821 0.13492 -0.0637 0.0248 1.0000
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Polar data table (+)
Polar graphs
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