St. CYR 172 (Royer) (stcyr172-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: St. CYR 172 (Royer) (stcyr172-il) Reynolds number: 100,000 Max Cl/Cd: 38.81 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-stcyr172-il-100000-n5.txt Download as CSV file: xf-stcyr172-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: St. CYR 172 (Royer)
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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9164 0.09012 0.08333 -0.0344 1.0000 0.0547
-15.250 -0.9503 0.08104 0.07400 -0.0401 1.0000 0.0546
-15.000 -0.9730 0.07431 0.06704 -0.0439 1.0000 0.0549
-14.750 -0.9900 0.06879 0.06130 -0.0468 1.0000 0.0552
-14.500 -1.0039 0.06400 0.05629 -0.0489 1.0000 0.0557
-14.250 -1.0145 0.05989 0.05197 -0.0504 1.0000 0.0562
-14.000 -1.0219 0.05635 0.04822 -0.0512 1.0000 0.0567
-13.750 -1.0279 0.05318 0.04482 -0.0515 1.0000 0.0572
-13.500 -1.0265 0.05067 0.04218 -0.0512 1.0000 0.0578
-13.250 -1.0176 0.04876 0.04027 -0.0505 1.0000 0.0585
-13.000 -1.0118 0.04683 0.03833 -0.0499 1.0000 0.0595
-12.750 -1.0074 0.04491 0.03634 -0.0491 1.0000 0.0604
-12.500 -1.0035 0.04303 0.03438 -0.0481 1.0000 0.0614
-12.250 -0.9997 0.04124 0.03249 -0.0470 1.0000 0.0626
-12.000 -0.9950 0.03957 0.03072 -0.0456 1.0000 0.0637
-11.750 -0.9896 0.03803 0.02904 -0.0439 1.0000 0.0648
-11.500 -0.9833 0.03661 0.02750 -0.0422 1.0000 0.0658
-11.250 -0.9781 0.03520 0.02607 -0.0401 1.0000 0.0668
-11.000 -0.9741 0.03389 0.02475 -0.0377 1.0000 0.0679
-10.750 -0.9704 0.03271 0.02354 -0.0349 1.0000 0.0692
-10.500 -0.9665 0.03164 0.02243 -0.0320 1.0000 0.0708
-10.250 -0.9623 0.03064 0.02137 -0.0288 1.0000 0.0727
-10.000 -0.9555 0.02967 0.02030 -0.0258 1.0000 0.0747
-9.750 -0.9490 0.02865 0.01928 -0.0229 1.0000 0.0767
-9.500 -0.9415 0.02768 0.01831 -0.0201 1.0000 0.0792
-9.250 -0.9317 0.02679 0.01738 -0.0174 1.0000 0.0822
-9.000 -0.9210 0.02593 0.01649 -0.0148 1.0000 0.0859
-8.750 -0.9105 0.02505 0.01565 -0.0122 1.0000 0.0912
-8.500 -0.8987 0.02424 0.01488 -0.0098 1.0000 0.0990
-8.250 -0.8860 0.02348 0.01419 -0.0074 1.0000 0.1110
-8.000 -0.8720 0.02281 0.01357 -0.0052 1.0000 0.1268
-7.750 -0.8567 0.02224 0.01300 -0.0031 1.0000 0.1432
-7.500 -0.8410 0.02173 0.01246 -0.0010 1.0000 0.1576
-7.250 -0.8249 0.02126 0.01198 0.0010 1.0000 0.1706
-7.000 -0.8081 0.02083 0.01153 0.0029 1.0000 0.1825
-6.750 -0.7912 0.02043 0.01110 0.0048 1.0000 0.1934
-6.500 -0.7746 0.02004 0.01073 0.0068 1.0000 0.2041
-6.250 -0.7574 0.01969 0.01038 0.0087 1.0000 0.2156
-6.000 -0.7398 0.01937 0.01004 0.0105 1.0000 0.2273
-5.750 -0.7229 0.01904 0.00976 0.0125 1.0000 0.2382
-5.500 -0.7054 0.01875 0.00948 0.0143 1.0000 0.2493
-5.250 -0.6872 0.01849 0.00920 0.0161 1.0000 0.2609
-5.000 -0.6698 0.01822 0.00899 0.0180 1.0000 0.2725
-4.750 -0.6521 0.01799 0.00880 0.0198 1.0000 0.2860
-4.500 -0.6342 0.01779 0.00863 0.0216 1.0000 0.3001
-4.250 -0.6160 0.01761 0.00847 0.0233 1.0000 0.3143
-4.000 -0.5833 0.01743 0.00831 0.0221 0.9951 0.3305
-3.750 -0.5414 0.01723 0.00812 0.0191 0.9856 0.3472
-3.500 -0.5035 0.01701 0.00791 0.0170 0.9766 0.3629
-3.250 -0.4661 0.01679 0.00773 0.0151 0.9681 0.3786
-3.000 -0.4300 0.01654 0.00753 0.0134 0.9585 0.3942
-2.750 -0.3948 0.01627 0.00732 0.0121 0.9479 0.4093
-2.500 -0.3577 0.01600 0.00712 0.0103 0.9381 0.4247
-2.250 -0.3182 0.01571 0.00689 0.0082 0.9285 0.4415
-2.000 -0.2817 0.01541 0.00669 0.0068 0.9167 0.4593
-1.750 -0.2432 0.01512 0.00651 0.0050 0.9048 0.4789
-1.500 -0.2053 0.01482 0.00634 0.0033 0.8913 0.5006
-1.250 -0.1708 0.01454 0.00619 0.0024 0.8744 0.5261
-1.000 -0.1396 0.01426 0.00610 0.0023 0.8535 0.5580
-0.750 -0.1080 0.01398 0.00601 0.0022 0.8296 0.5991
-0.500 -0.0780 0.01372 0.00595 0.0025 0.7995 0.6434
-0.250 -0.0409 0.01351 0.00583 0.0016 0.7653 0.6871
0.000 0.0000 0.01341 0.00576 0.0000 0.7276 0.7277
0.250 0.0409 0.01351 0.00583 -0.0015 0.6871 0.7652
0.500 0.0779 0.01372 0.00595 -0.0025 0.6430 0.7994
0.750 0.1080 0.01398 0.00601 -0.0022 0.5989 0.8296
1.000 0.1396 0.01426 0.00610 -0.0023 0.5578 0.8535
1.250 0.1707 0.01454 0.00619 -0.0024 0.5259 0.8744
1.500 0.2054 0.01482 0.00634 -0.0034 0.5008 0.8913
1.750 0.2433 0.01512 0.00651 -0.0050 0.4789 0.9049
2.000 0.2818 0.01541 0.00669 -0.0068 0.4595 0.9167
2.250 0.3181 0.01571 0.00689 -0.0082 0.4417 0.9285
2.500 0.3576 0.01600 0.00711 -0.0103 0.4249 0.9380
2.750 0.3949 0.01627 0.00732 -0.0121 0.4094 0.9479
3.000 0.4301 0.01654 0.00753 -0.0134 0.3941 0.9585
3.250 0.4661 0.01679 0.00773 -0.0151 0.3786 0.9682
3.500 0.5036 0.01701 0.00791 -0.0171 0.3629 0.9767
3.750 0.5415 0.01723 0.00812 -0.0191 0.3472 0.9856
4.000 0.5834 0.01743 0.00831 -0.0221 0.3305 0.9951
4.250 0.6160 0.01761 0.00847 -0.0233 0.3144 1.0000
4.500 0.6342 0.01779 0.00863 -0.0216 0.3002 1.0000
4.750 0.6521 0.01799 0.00879 -0.0198 0.2860 1.0000
5.000 0.6697 0.01822 0.00899 -0.0180 0.2725 1.0000
5.250 0.6871 0.01848 0.00919 -0.0161 0.2608 1.0000
5.500 0.7053 0.01875 0.00948 -0.0143 0.2493 1.0000
5.750 0.7229 0.01904 0.00976 -0.0125 0.2382 1.0000
6.000 0.7398 0.01937 0.01004 -0.0105 0.2272 1.0000
6.250 0.7574 0.01969 0.01038 -0.0087 0.2157 1.0000
6.500 0.7745 0.02004 0.01073 -0.0068 0.2039 1.0000
6.750 0.7911 0.02043 0.01110 -0.0048 0.1933 1.0000
7.000 0.8080 0.02083 0.01152 -0.0029 0.1823 1.0000
7.250 0.8248 0.02125 0.01198 -0.0010 0.1703 1.0000
7.500 0.8409 0.02173 0.01246 0.0010 0.1576 1.0000
7.750 0.8567 0.02224 0.01300 0.0031 0.1433 1.0000
8.000 0.8720 0.02281 0.01357 0.0052 0.1268 1.0000
8.250 0.8859 0.02349 0.01419 0.0074 0.1105 1.0000
8.500 0.8986 0.02425 0.01488 0.0098 0.0986 1.0000
8.750 0.9105 0.02506 0.01565 0.0122 0.0909 1.0000
9.000 0.9210 0.02593 0.01649 0.0148 0.0858 1.0000
9.250 0.9318 0.02679 0.01738 0.0174 0.0823 1.0000
9.500 0.9415 0.02768 0.01831 0.0201 0.0792 1.0000
9.750 0.9492 0.02865 0.01928 0.0229 0.0767 1.0000
10.000 0.9556 0.02968 0.02030 0.0258 0.0747 1.0000
10.250 0.9624 0.03065 0.02137 0.0287 0.0725 1.0000
10.500 0.9668 0.03164 0.02243 0.0319 0.0708 1.0000
10.750 0.9708 0.03271 0.02354 0.0349 0.0693 1.0000
11.000 0.9744 0.03390 0.02476 0.0376 0.0679 1.0000
11.250 0.9785 0.03521 0.02607 0.0400 0.0668 1.0000
11.500 0.9840 0.03660 0.02747 0.0421 0.0658 1.0000
11.750 0.9901 0.03803 0.02904 0.0439 0.0648 1.0000
12.000 0.9957 0.03957 0.03071 0.0455 0.0637 1.0000
12.250 1.0001 0.04124 0.03250 0.0469 0.0625 1.0000
12.500 1.0046 0.04301 0.03436 0.0481 0.0615 1.0000
12.750 1.0082 0.04489 0.03632 0.0490 0.0604 1.0000
13.000 1.0128 0.04681 0.03830 0.0498 0.0594 1.0000
13.250 1.0188 0.04875 0.04026 0.0505 0.0586 1.0000
13.500 1.0277 0.05064 0.04216 0.0511 0.0578 1.0000
13.750 1.0289 0.05317 0.04481 0.0514 0.0572 1.0000
14.000 1.0235 0.05630 0.04816 0.0511 0.0567 1.0000
14.250 1.0154 0.05991 0.05200 0.0502 0.0562 1.0000
14.500 1.0047 0.06403 0.05633 0.0487 0.0557 1.0000
14.750 0.9919 0.06872 0.06123 0.0467 0.0553 1.0000
15.000 0.9746 0.07428 0.06701 0.0438 0.0549 1.0000
15.250 0.9517 0.08106 0.07402 0.0399 0.0547 1.0000
15.500 0.9175 0.09017 0.08339 0.0342 0.0546 1.0000
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Polar data table (+)
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