St. CYR 171 (Royer) (stcyr171-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: St. CYR 171 (Royer) (stcyr171-il) Reynolds number: 200,000 Max Cl/Cd: 47.55 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-stcyr171-il-200000.txt Download as CSV file: xf-stcyr171-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: St. CYR 171 (Royer)
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8886 0.07698 0.07252 -0.0375 1.0000 0.0458
-13.500 -0.9255 0.06850 0.06388 -0.0432 1.0000 0.0455
-13.250 -0.9528 0.06165 0.05688 -0.0478 1.0000 0.0452
-13.000 -0.9781 0.05569 0.05073 -0.0516 1.0000 0.0450
-12.750 -1.0013 0.05109 0.04590 -0.0531 1.0000 0.0450
-12.500 -1.0193 0.04769 0.04229 -0.0519 1.0000 0.0450
-12.250 -1.0333 0.04499 0.03937 -0.0491 1.0000 0.0450
-12.000 -1.0421 0.04256 0.03670 -0.0460 1.0000 0.0452
-11.750 -1.0445 0.04041 0.03427 -0.0434 1.0000 0.0456
-11.500 -1.0424 0.03854 0.03213 -0.0408 1.0000 0.0460
-11.250 -1.0395 0.03557 0.02898 -0.0384 1.0000 0.0467
-11.000 -1.0298 0.03369 0.02703 -0.0363 1.0000 0.0475
-10.750 -1.0183 0.03219 0.02544 -0.0342 1.0000 0.0483
-10.500 -1.0061 0.03078 0.02393 -0.0321 1.0000 0.0490
-10.250 -0.9930 0.02947 0.02251 -0.0300 1.0000 0.0497
-10.000 -0.9792 0.02825 0.02118 -0.0279 1.0000 0.0506
-9.750 -0.9647 0.02715 0.01995 -0.0259 1.0000 0.0517
-9.500 -0.9495 0.02613 0.01881 -0.0238 1.0000 0.0529
-9.250 -0.9337 0.02519 0.01774 -0.0218 1.0000 0.0538
-9.000 -0.9212 0.02403 0.01656 -0.0192 1.0000 0.0549
-8.750 -0.9073 0.02307 0.01560 -0.0168 1.0000 0.0561
-8.500 -0.8915 0.02227 0.01477 -0.0147 1.0000 0.0576
-8.250 -0.8747 0.02154 0.01400 -0.0126 1.0000 0.0594
-8.000 -0.8569 0.02089 0.01328 -0.0107 1.0000 0.0617
-7.750 -0.8400 0.02019 0.01254 -0.0087 1.0000 0.0643
-7.500 -0.8225 0.01952 0.01190 -0.0068 1.0000 0.0680
-7.250 -0.8037 0.01896 0.01129 -0.0050 1.0000 0.0727
-7.000 -0.7856 0.01833 0.01075 -0.0031 1.0000 0.0813
-6.750 -0.7663 0.01778 0.01030 -0.0014 1.0000 0.0992
-6.500 -0.7438 0.01745 0.01005 -0.0004 1.0000 0.1215
-6.250 -0.7202 0.01725 0.00984 0.0004 1.0000 0.1362
-6.000 -0.6976 0.01704 0.00960 0.0015 1.0000 0.1463
-5.750 -0.6749 0.01687 0.00939 0.0025 1.0000 0.1546
-5.500 -0.6536 0.01662 0.00912 0.0038 1.0000 0.1618
-5.250 -0.6322 0.01642 0.00892 0.0050 1.0000 0.1685
-5.000 -0.6103 0.01624 0.00866 0.0062 1.0000 0.1745
-4.750 -0.5909 0.01597 0.00844 0.0079 1.0000 0.1803
-4.500 -0.5697 0.01582 0.00829 0.0091 1.0000 0.1877
-4.250 -0.5495 0.01564 0.00810 0.0106 1.0000 0.1943
-4.000 -0.5299 0.01549 0.00800 0.0121 1.0000 0.2006
-3.750 -0.5100 0.01539 0.00786 0.0136 1.0000 0.2076
-3.500 -0.4917 0.01528 0.00780 0.0152 1.0000 0.2144
-3.250 -0.4731 0.01524 0.00777 0.0168 1.0000 0.2232
-3.000 -0.4382 0.01518 0.00776 0.0150 0.9958 0.2351
-2.750 -0.3964 0.01509 0.00772 0.0119 0.9890 0.2503
-2.500 -0.3539 0.01508 0.00779 0.0089 0.9821 0.2669
-2.250 -0.3150 0.01514 0.00796 0.0067 0.9732 0.2839
-2.000 -0.2706 0.01548 0.00851 0.0035 0.9669 0.3067
-1.750 -0.2312 0.01691 0.01050 0.0021 0.9560 0.3355
-1.500 -0.1795 0.01885 0.01235 -0.0016 0.9472 0.4221
-1.250 -0.1311 0.01926 0.01282 -0.0049 0.9373 0.4387
-1.000 -0.0900 0.01931 0.01286 -0.0068 0.9248 0.4573
-0.750 -0.0521 0.01839 0.01193 -0.0086 0.9132 0.4869
-0.500 -0.0247 0.01536 0.00879 -0.0091 0.9001 0.5375
-0.250 0.0070 0.01379 0.00713 -0.0100 0.8826 0.5579
0.000 0.0402 0.01263 0.00591 -0.0109 0.8616 0.5709
0.250 0.0716 0.01195 0.00518 -0.0113 0.8361 0.5803
0.500 0.1035 0.01127 0.00450 -0.0118 0.8120 0.5897
0.750 0.1345 0.01073 0.00405 -0.0122 0.7877 0.5981
1.000 0.1627 0.01039 0.00382 -0.0119 0.7611 0.6059
1.250 0.1888 0.01018 0.00371 -0.0111 0.7352 0.6143
1.500 0.2112 0.01007 0.00380 -0.0095 0.7090 0.6268
1.750 0.2329 0.01012 0.00398 -0.0076 0.6804 0.6464
2.000 0.2562 0.01022 0.00403 -0.0063 0.6453 0.6667
2.500 0.3008 0.01062 0.00403 -0.0032 0.5408 0.6845
2.750 0.3202 0.01107 0.00411 -0.0012 0.4593 0.6924
3.000 0.3361 0.01176 0.00423 0.0011 0.3398 0.6989
3.250 0.3563 0.01238 0.00453 0.0025 0.2958 0.7049
3.500 0.3795 0.01281 0.00483 0.0034 0.2727 0.7098
3.750 0.4032 0.01321 0.00514 0.0043 0.2571 0.7151
4.000 0.4275 0.01359 0.00544 0.0050 0.2440 0.7204
4.250 0.4527 0.01390 0.00577 0.0056 0.2331 0.7248
4.500 0.4772 0.01431 0.00610 0.0063 0.2225 0.7293
4.750 0.5027 0.01452 0.00637 0.0068 0.2126 0.7347
5.000 0.5275 0.01496 0.00675 0.0074 0.2043 0.7389
5.250 0.5534 0.01520 0.00707 0.0079 0.1972 0.7419
5.500 0.5787 0.01557 0.00742 0.0083 0.1904 0.7459
5.750 0.6044 0.01592 0.00784 0.0088 0.1842 0.7505
6.000 0.6301 0.01617 0.00817 0.0092 0.1778 0.7566
6.250 0.6554 0.01661 0.00859 0.0096 0.1707 0.7664
6.500 0.6809 0.01660 0.00881 0.0102 0.1633 0.7776
6.750 0.7067 0.01675 0.00909 0.0105 0.1560 0.7985
7.000 0.7391 0.01691 0.00949 0.0096 0.1475 0.8353
7.250 0.7687 0.01714 0.00974 0.0090 0.1373 0.8588
7.500 0.7976 0.01717 0.00989 0.0088 0.1225 0.8743
7.750 0.8255 0.01736 0.01012 0.0087 0.0978 0.8855
8.000 0.8485 0.01810 0.01072 0.0093 0.0804 0.8936
8.250 0.8695 0.01884 0.01143 0.0104 0.0723 0.8970
8.500 0.8874 0.01963 0.01224 0.0122 0.0682 0.8956
8.750 0.9159 0.02048 0.01316 0.0116 0.0642 0.9131
9.000 0.9257 0.02125 0.01389 0.0148 0.0618 0.8995
9.250 0.9331 0.02213 0.01475 0.0186 0.0600 0.8781
9.500 0.9432 0.02284 0.01551 0.0219 0.0583 0.8492
9.750 0.9563 0.02371 0.01641 0.0244 0.0568 0.8247
10.000 0.9716 0.02469 0.01739 0.0263 0.0554 0.8083
10.250 0.9879 0.02576 0.01845 0.0279 0.0541 0.7964
10.500 1.0044 0.02710 0.01970 0.0293 0.0527 0.7815
10.750 1.0217 0.02892 0.02154 0.0304 0.0514 0.7713
11.000 1.0368 0.03010 0.02288 0.0320 0.0504 0.7666
11.250 1.0510 0.03154 0.02448 0.0336 0.0495 0.7626
11.500 1.0636 0.03306 0.02615 0.0353 0.0487 0.7591
11.750 1.0732 0.03468 0.02793 0.0374 0.0479 0.7561
12.000 1.0795 0.03626 0.02967 0.0398 0.0472 0.7538
12.250 1.0846 0.03785 0.03138 0.0422 0.0464 0.7517
12.500 1.0896 0.03954 0.03317 0.0443 0.0457 0.7496
12.750 1.0937 0.04159 0.03530 0.0462 0.0450 0.7474
13.000 1.0949 0.04433 0.03815 0.0477 0.0442 0.7454
13.250 1.0846 0.04771 0.04176 0.0497 0.0439 0.7441
13.500 1.0702 0.05084 0.04510 0.0514 0.0438 0.7427
13.750 1.0522 0.05421 0.04870 0.0522 0.0437 0.7416
14.000 1.0352 0.05817 0.05286 0.0518 0.0437 0.7406
14.500 0.9894 0.06870 0.06381 0.0476 0.0438 0.7388
14.750 0.9624 0.07518 0.07050 0.0431 0.0441 0.7385
15.000 0.6308 0.16220 0.15834 -0.0110 0.0776 0.7937
|
Polar data table (+)
Polar graphs
<< Back to St. CYR 171 (Royer) (stcyr171-il)