St. CYR 171 (Royer) (stcyr171-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: St. CYR 171 (Royer) (stcyr171-il) Reynolds number: 500,000 Max Cl/Cd: 42.97 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-stcyr171-il-500000.txt Download as CSV file: xf-stcyr171-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8854 0.11419 0.11128 -0.0105 1.0000 0.0259
-16.000 -0.9458 0.09723 0.09408 -0.0212 1.0000 0.0254
-15.750 -0.9853 0.08512 0.08175 -0.0292 1.0000 0.0251
-15.500 -1.0073 0.07754 0.07401 -0.0343 1.0000 0.0253
-15.250 -1.0350 0.07018 0.06646 -0.0386 1.0000 0.0250
-15.000 -1.0502 0.06520 0.06137 -0.0415 1.0000 0.0253
-14.750 -1.0675 0.06004 0.05607 -0.0444 1.0000 0.0253
-14.500 -1.0805 0.05544 0.05134 -0.0471 1.0000 0.0255
-14.250 -1.0930 0.05079 0.04655 -0.0503 1.0000 0.0257
-14.000 -1.1044 0.04669 0.04230 -0.0526 1.0000 0.0258
-13.750 -1.1134 0.04341 0.03887 -0.0536 1.0000 0.0260
-13.500 -1.1215 0.04082 0.03611 -0.0530 1.0000 0.0263
-13.250 -1.1257 0.03885 0.03399 -0.0513 1.0000 0.0264
-13.000 -1.1289 0.03723 0.03223 -0.0487 1.0000 0.0266
-12.750 -1.1301 0.03609 0.03093 -0.0455 1.0000 0.0269
-12.500 -1.1253 0.03503 0.02971 -0.0431 1.0000 0.0271
-12.250 -1.1283 0.03223 0.02680 -0.0397 1.0000 0.0276
-12.000 -1.1233 0.03059 0.02514 -0.0370 1.0000 0.0281
-11.750 -1.1141 0.02940 0.02391 -0.0347 1.0000 0.0286
-11.500 -1.1030 0.02833 0.02278 -0.0325 1.0000 0.0291
-11.250 -1.0911 0.02730 0.02168 -0.0303 1.0000 0.0297
-11.000 -1.0783 0.02632 0.02064 -0.0281 1.0000 0.0302
-10.750 -1.0648 0.02540 0.01962 -0.0260 1.0000 0.0306
-10.500 -1.0505 0.02452 0.01867 -0.0239 1.0000 0.0311
-10.250 -1.0352 0.02373 0.01779 -0.0219 1.0000 0.0316
-10.000 -1.0183 0.02304 0.01702 -0.0201 1.0000 0.0321
-9.750 -0.9994 0.02249 0.01639 -0.0186 1.0000 0.0325
-9.500 -0.9904 0.02128 0.01510 -0.0155 1.0000 0.0331
-9.250 -0.9781 0.02033 0.01410 -0.0128 1.0000 0.0336
-9.000 -0.9633 0.01954 0.01328 -0.0105 1.0000 0.0343
-8.750 -0.9467 0.01888 0.01257 -0.0085 1.0000 0.0348
-8.500 -0.9292 0.01827 0.01193 -0.0066 1.0000 0.0355
-8.250 -0.9110 0.01772 0.01133 -0.0048 1.0000 0.0363
-8.000 -0.8921 0.01721 0.01077 -0.0031 1.0000 0.0371
-7.750 -0.8728 0.01674 0.01025 -0.0014 1.0000 0.0378
-7.500 -0.8531 0.01630 0.00976 0.0002 1.0000 0.0384
-7.250 -0.8329 0.01591 0.00931 0.0018 1.0000 0.0388
-7.000 -0.8142 0.01539 0.00875 0.0036 1.0000 0.0400
-6.750 -0.7945 0.01497 0.00831 0.0052 1.0000 0.0413
-6.500 -0.7743 0.01460 0.00792 0.0068 1.0000 0.0430
-6.250 -0.7536 0.01430 0.00760 0.0083 1.0000 0.0446
-6.000 -0.7328 0.01403 0.00731 0.0097 1.0000 0.0471
-5.750 -0.7126 0.01374 0.00707 0.0113 1.0000 0.0531
-5.500 -0.6925 0.01338 0.00696 0.0128 0.9998 0.0868
-5.250 -0.6545 0.01320 0.00691 0.0106 0.9968 0.1095
-5.000 -0.6154 0.01309 0.00686 0.0082 0.9937 0.1236
-4.750 -0.5789 0.01295 0.00676 0.0064 0.9902 0.1330
-4.500 -0.5424 0.01283 0.00664 0.0047 0.9865 0.1406
-4.250 -0.5048 0.01269 0.00655 0.0026 0.9833 0.1491
-4.000 -0.4656 0.01258 0.00646 0.0003 0.9810 0.1563
-3.750 -0.4336 0.01241 0.00632 -0.0004 0.9749 0.1636
-3.500 -0.3964 0.01226 0.00622 -0.0022 0.9707 0.1724
-3.250 -0.3571 0.01210 0.00613 -0.0045 0.9677 0.1830
-3.000 -0.3253 0.01191 0.00601 -0.0052 0.9600 0.1950
-2.750 -0.2876 0.01171 0.00588 -0.0070 0.9547 0.2097
-2.500 -0.2513 0.01146 0.00570 -0.0085 0.9450 0.2253
-2.250 -0.2082 0.01121 0.00551 -0.0115 0.9354 0.2420
-2.000 -0.1688 0.01097 0.00533 -0.0137 0.9201 0.2587
-1.750 -0.1256 0.01081 0.00520 -0.0167 0.8998 0.2751
-1.500 -0.0900 0.01083 0.00522 -0.0180 0.8711 0.2886
-1.250 -0.0585 0.01118 0.00560 -0.0182 0.8381 0.3058
-1.000 -0.0267 0.01287 0.00759 -0.0179 0.8062 0.3334
-0.750 0.0018 0.01324 0.00782 -0.0176 0.7791 0.4018
-0.250 0.0563 0.01439 0.00879 -0.0162 0.7287 0.4159
0.000 0.0837 0.01493 0.00923 -0.0157 0.7065 0.4221
0.250 0.1092 0.01506 0.00936 -0.0149 0.6848 0.4258
0.500 0.1367 0.01584 0.01003 -0.0142 0.6577 0.4334
0.750 0.1596 0.01556 0.00973 -0.0130 0.6243 0.4396
1.000 0.1882 0.01746 0.01145 -0.0122 0.5819 0.4554
1.250 0.2072 0.01609 0.00997 -0.0108 0.5475 0.4572
1.500 0.2295 0.01578 0.00954 -0.0097 0.5130 0.4603
1.750 0.2549 0.01633 0.00993 -0.0089 0.4687 0.4645
2.000 0.2788 0.01781 0.01095 -0.0078 0.3580 0.4656
2.250 0.3019 0.01888 0.01163 -0.0067 0.2813 0.4659
2.500 0.3207 0.01744 0.01008 -0.0055 0.2505 0.4670
2.750 0.3435 0.01708 0.00963 -0.0046 0.2291 0.4683
3.000 0.3682 0.01703 0.00952 -0.0040 0.2146 0.4692
3.250 0.3932 0.01709 0.00953 -0.0034 0.2025 0.4694
3.500 0.4184 0.01716 0.00954 -0.0028 0.1920 0.4696
3.750 0.4438 0.01720 0.00957 -0.0022 0.1841 0.4698
4.000 0.4692 0.01723 0.00959 -0.0016 0.1767 0.4702
4.250 0.4940 0.01734 0.00966 -0.0010 0.1696 0.4704
4.500 0.5199 0.01735 0.00968 -0.0005 0.1638 0.4706
4.750 0.5449 0.01744 0.00975 0.0001 0.1573 0.4707
5.000 0.5701 0.01751 0.00982 0.0007 0.1515 0.4707
5.250 0.5958 0.01754 0.00987 0.0012 0.1464 0.4706
5.500 0.6207 0.01763 0.00994 0.0019 0.1406 0.4705
5.750 0.6458 0.01771 0.01004 0.0025 0.1354 0.4704
6.000 0.6715 0.01772 0.01007 0.0029 0.1283 0.4706
6.250 0.6962 0.01781 0.01014 0.0036 0.1206 0.4706
6.500 0.7212 0.01789 0.01019 0.0042 0.1093 0.4707
6.750 0.7453 0.01806 0.01029 0.0049 0.0933 0.4706
7.000 0.7662 0.01854 0.01056 0.0061 0.0604 0.4707
7.250 0.7874 0.01898 0.01092 0.0073 0.0495 0.4708
7.500 0.8093 0.01935 0.01129 0.0084 0.0459 0.4709
7.750 0.8310 0.01973 0.01170 0.0095 0.0434 0.4711
8.000 0.8531 0.02005 0.01207 0.0106 0.0421 0.4714
8.250 0.8744 0.02043 0.01250 0.0117 0.0407 0.4718
8.500 0.8951 0.02083 0.01296 0.0130 0.0396 0.4718
8.750 0.9143 0.02135 0.01351 0.0144 0.0385 0.4717
9.000 0.9312 0.02202 0.01422 0.0162 0.0375 0.4715
9.250 0.9482 0.02266 0.01493 0.0180 0.0367 0.4714
9.500 0.9675 0.02308 0.01543 0.0194 0.0361 0.4713
9.750 0.9857 0.02358 0.01600 0.0210 0.0354 0.4713
10.000 1.0027 0.02414 0.01663 0.0227 0.0347 0.4712
10.250 1.0187 0.02475 0.01730 0.0245 0.0341 0.4712
10.500 1.0338 0.02539 0.01801 0.0264 0.0335 0.4711
10.750 1.0474 0.02609 0.01875 0.0285 0.0328 0.4711
11.000 1.0579 0.02686 0.01957 0.0310 0.0322 0.4710
11.250 1.0648 0.02789 0.02064 0.0340 0.0315 0.4710
11.500 1.0710 0.02948 0.02230 0.0367 0.0309 0.4710
11.750 1.0811 0.03000 0.02293 0.0393 0.0305 0.4710
12.000 1.0910 0.03081 0.02385 0.0416 0.0302 0.4710
12.250 1.1000 0.03169 0.02483 0.0439 0.0298 0.4710
12.500 1.1079 0.03270 0.02594 0.0461 0.0293 0.4710
12.750 1.1144 0.03384 0.02717 0.0483 0.0289 0.4710
13.000 1.1207 0.03491 0.02833 0.0502 0.0284 0.4710
13.250 1.1249 0.03615 0.02964 0.0522 0.0279 0.4711
13.500 1.1285 0.03749 0.03107 0.0538 0.0274 0.4711
13.750 1.1314 0.03901 0.03265 0.0553 0.0269 0.4711
14.000 1.1343 0.04066 0.03436 0.0565 0.0266 0.4711
14.250 1.1365 0.04279 0.03654 0.0575 0.0262 0.4712
14.500 1.1338 0.04612 0.04000 0.0583 0.0257 0.4712
14.750 1.1265 0.04858 0.04260 0.0589 0.0256 0.4712
15.000 1.1198 0.05121 0.04538 0.0589 0.0254 0.4711
15.250 1.1122 0.05409 0.04841 0.0584 0.0253 0.4712
15.500 1.1029 0.05753 0.05200 0.0574 0.0251 0.4712
15.750 1.0918 0.06146 0.05609 0.0557 0.0249 0.4711
16.000 1.0789 0.06604 0.06082 0.0536 0.0248 0.4711
16.250 1.0645 0.07110 0.06603 0.0508 0.0247 0.4710
16.500 1.0478 0.07691 0.07199 0.0473 0.0247 0.4709
16.750 1.0274 0.08380 0.07905 0.0428 0.0245 0.4708
17.000 1.0039 0.09183 0.08725 0.0375 0.0245 0.4707
17.250 0.9748 0.10150 0.09709 0.0310 0.0246 0.4706
17.500 0.9352 0.11397 0.10975 0.0226 0.0247 0.4704
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Polar data table (+)
Polar graphs
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