S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9033 (7.5%) (s9033-il) Reynolds number: 100,000 Max Cl/Cd: 32.28 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9033-il-100000-n5.txt Download as CSV file: xf-s9033-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9033 (7.5%)
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7723 0.08292 0.07796 0.0056 1.0000 0.0339
-10.000 -0.8241 0.06531 0.06036 -0.0098 1.0000 0.0325
-9.750 -0.8586 0.05781 0.05265 -0.0141 1.0000 0.0320
-9.500 -0.8762 0.05187 0.04634 -0.0155 1.0000 0.0320
-9.250 -0.8819 0.04688 0.04093 -0.0157 1.0000 0.0324
-9.000 -0.8795 0.04260 0.03617 -0.0154 1.0000 0.0331
-8.750 -0.8709 0.03896 0.03205 -0.0149 1.0000 0.0342
-8.500 -0.8578 0.03600 0.02856 -0.0142 1.0000 0.0361
-8.250 -0.8413 0.03346 0.02547 -0.0134 1.0000 0.0376
-8.000 -0.8237 0.03083 0.02261 -0.0127 1.0000 0.0390
-7.750 -0.8034 0.02901 0.02063 -0.0120 1.0000 0.0406
-7.500 -0.7821 0.02736 0.01878 -0.0113 1.0000 0.0427
-7.250 -0.7600 0.02576 0.01694 -0.0105 1.0000 0.0452
-7.000 -0.7369 0.02439 0.01525 -0.0098 1.0000 0.0486
-6.750 -0.7149 0.02315 0.01402 -0.0092 1.0000 0.0531
-6.500 -0.6914 0.02209 0.01282 -0.0085 1.0000 0.0586
-6.250 -0.6685 0.02091 0.01152 -0.0077 1.0000 0.0639
-6.000 -0.6445 0.02010 0.01062 -0.0071 1.0000 0.0724
-5.750 -0.6209 0.01927 0.00979 -0.0065 1.0000 0.0817
-5.500 -0.5969 0.01849 0.00898 -0.0059 1.0000 0.0923
-5.250 -0.5726 0.01780 0.00827 -0.0053 1.0000 0.1051
-5.000 -0.5483 0.01714 0.00759 -0.0047 1.0000 0.1197
-4.750 -0.5238 0.01652 0.00699 -0.0041 1.0000 0.1364
-4.500 -0.4991 0.01594 0.00641 -0.0035 1.0000 0.1543
-4.250 -0.4746 0.01538 0.00594 -0.0029 1.0000 0.1766
-4.000 -0.4500 0.01486 0.00548 -0.0024 1.0000 0.2026
-3.750 -0.4254 0.01438 0.00510 -0.0018 1.0000 0.2316
-3.500 -0.4008 0.01392 0.00476 -0.0011 1.0000 0.2661
-3.250 -0.3765 0.01347 0.00447 -0.0005 1.0000 0.3058
-3.000 -0.3523 0.01304 0.00421 0.0002 1.0000 0.3503
-2.750 -0.3282 0.01262 0.00398 0.0010 1.0000 0.3988
-2.500 -0.3043 0.01223 0.00380 0.0019 1.0000 0.4497
-2.250 -0.2806 0.01186 0.00365 0.0029 1.0000 0.5034
-2.000 -0.2570 0.01151 0.00354 0.0040 1.0000 0.5616
-1.750 -0.2338 0.01118 0.00344 0.0053 1.0000 0.6230
-1.500 -0.2111 0.01088 0.00339 0.0069 1.0000 0.6863
-1.250 -0.1883 0.01062 0.00337 0.0085 1.0000 0.7515
-1.000 -0.1619 0.01042 0.00338 0.0096 1.0000 0.8210
-0.750 -0.1216 0.01033 0.00342 0.0078 1.0000 0.8952
-0.500 -0.0709 0.01029 0.00341 0.0035 1.0000 0.9568
-0.250 -0.0197 0.01026 0.00335 -0.0013 1.0000 0.9990
0.000 0.0000 0.01025 0.00333 0.0000 1.0000 1.0000
0.250 0.0198 0.01026 0.00335 0.0013 0.9989 1.0000
0.500 0.0710 0.01029 0.00341 -0.0035 0.9568 1.0000
0.750 0.1216 0.01033 0.00342 -0.0079 0.8950 1.0000
1.000 0.1620 0.01042 0.00338 -0.0096 0.8209 1.0000
1.250 0.1883 0.01062 0.00337 -0.0085 0.7514 1.0000
1.500 0.2112 0.01088 0.00339 -0.0069 0.6864 1.0000
1.750 0.2339 0.01118 0.00344 -0.0053 0.6228 1.0000
2.000 0.2571 0.01151 0.00354 -0.0040 0.5615 1.0000
2.250 0.2807 0.01186 0.00365 -0.0029 0.5034 1.0000
2.500 0.3044 0.01223 0.00380 -0.0020 0.4497 1.0000
2.750 0.3283 0.01262 0.00398 -0.0011 0.3987 1.0000
3.000 0.3523 0.01303 0.00422 -0.0003 0.3504 1.0000
3.250 0.3766 0.01347 0.00447 0.0005 0.3059 1.0000
3.500 0.4009 0.01392 0.00476 0.0011 0.2661 1.0000
3.750 0.4254 0.01438 0.00510 0.0017 0.2317 1.0000
4.000 0.4501 0.01486 0.00548 0.0023 0.2025 1.0000
4.250 0.4747 0.01538 0.00594 0.0029 0.1766 1.0000
4.500 0.4992 0.01594 0.00641 0.0035 0.1543 1.0000
4.750 0.5238 0.01652 0.00699 0.0041 0.1365 1.0000
5.000 0.5483 0.01714 0.00759 0.0047 0.1197 1.0000
5.250 0.5726 0.01780 0.00827 0.0053 0.1051 1.0000
5.500 0.5968 0.01849 0.00897 0.0059 0.0922 1.0000
5.750 0.6208 0.01927 0.00979 0.0065 0.0817 1.0000
6.000 0.6445 0.02010 0.01062 0.0071 0.0723 1.0000
6.250 0.6684 0.02091 0.01152 0.0077 0.0639 1.0000
6.500 0.6914 0.02209 0.01282 0.0085 0.0586 1.0000
6.750 0.7148 0.02316 0.01403 0.0092 0.0532 1.0000
7.000 0.7368 0.02439 0.01525 0.0098 0.0487 1.0000
7.250 0.7599 0.02576 0.01693 0.0106 0.0452 1.0000
7.500 0.7819 0.02736 0.01878 0.0113 0.0427 1.0000
7.750 0.8033 0.02901 0.02062 0.0120 0.0406 1.0000
8.000 0.8235 0.03082 0.02259 0.0127 0.0391 1.0000
8.250 0.8411 0.03345 0.02545 0.0134 0.0376 1.0000
8.500 0.8576 0.03598 0.02854 0.0142 0.0361 1.0000
8.750 0.8707 0.03895 0.03204 0.0149 0.0342 1.0000
9.000 0.8793 0.04259 0.03616 0.0155 0.0331 1.0000
9.250 0.8818 0.04686 0.04090 0.0158 0.0324 1.0000
9.500 0.8761 0.05184 0.04631 0.0155 0.0320 1.0000
9.750 0.8588 0.05776 0.05259 0.0141 0.0320 1.0000
10.000 0.8241 0.06533 0.06038 0.0098 0.0325 1.0000
10.250 0.7722 0.08308 0.07811 -0.0057 0.0339 1.0000
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Polar data table (+)
Polar graphs
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