S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9026 (9.5%) (s9026-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.15 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9026-il-1000000.txt Download as CSV file: xf-s9026-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S9026 (9.5%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.0991 0.10861 0.10622 0.0084 1.0000 0.0072
-17.000 -1.1342 0.09745 0.09494 0.0018 1.0000 0.0071
-16.750 -1.1829 0.08437 0.08169 -0.0059 1.0000 0.0069
-16.500 -1.2138 0.07472 0.07190 -0.0117 1.0000 0.0069
-16.250 -1.2558 0.06329 0.06028 -0.0188 1.0000 0.0067
-16.000 -1.2897 0.05360 0.05038 -0.0251 1.0000 0.0066
-15.750 -1.3144 0.04609 0.04267 -0.0299 1.0000 0.0065
-15.500 -1.3236 0.04157 0.03803 -0.0323 1.0000 0.0067
-15.250 -1.3257 0.03842 0.03477 -0.0336 1.0000 0.0068
-15.000 -1.3317 0.03525 0.03148 -0.0342 1.0000 0.0070
-14.750 -1.3344 0.03280 0.02891 -0.0340 1.0000 0.0072
-14.500 -1.3340 0.03093 0.02693 -0.0331 1.0000 0.0073
-14.250 -1.3323 0.02935 0.02525 -0.0316 1.0000 0.0075
-14.000 -1.3253 0.02828 0.02409 -0.0300 1.0000 0.0077
-13.750 -1.3195 0.02722 0.02294 -0.0279 1.0000 0.0078
-13.500 -1.3286 0.02538 0.02095 -0.0238 1.0000 0.0082
-13.250 -1.3193 0.02423 0.01973 -0.0220 1.0000 0.0087
-13.000 -1.3036 0.02346 0.01891 -0.0207 1.0000 0.0091
-12.750 -1.2853 0.02285 0.01826 -0.0197 1.0000 0.0096
-12.500 -1.2658 0.02231 0.01766 -0.0188 1.0000 0.0101
-12.250 -1.2462 0.02173 0.01700 -0.0179 1.0000 0.0106
-12.000 -1.2237 0.02140 0.01663 -0.0173 1.0000 0.0109
-11.750 -1.2124 0.01990 0.01499 -0.0155 1.0000 0.0118
-11.500 -1.1923 0.01924 0.01431 -0.0147 1.0000 0.0124
-11.250 -1.1705 0.01875 0.01378 -0.0140 1.0000 0.0130
-11.000 -1.1486 0.01823 0.01320 -0.0132 1.0000 0.0136
-10.750 -1.1260 0.01777 0.01270 -0.0126 1.0000 0.0142
-10.500 -1.1026 0.01738 0.01224 -0.0120 1.0000 0.0147
-10.250 -1.0801 0.01687 0.01167 -0.0113 1.0000 0.0150
-10.000 -1.0624 0.01574 0.01043 -0.0100 1.0000 0.0163
-9.750 -1.0399 0.01519 0.00986 -0.0093 1.0000 0.0172
-9.500 -1.0166 0.01473 0.00935 -0.0086 1.0000 0.0179
-9.250 -0.9930 0.01429 0.00887 -0.0080 1.0000 0.0187
-9.000 -0.9690 0.01391 0.00844 -0.0074 1.0000 0.0194
-8.750 -0.9446 0.01358 0.00806 -0.0068 1.0000 0.0199
-8.500 -0.9227 0.01290 0.00730 -0.0058 1.0000 0.0211
-8.250 -0.9000 0.01234 0.00672 -0.0049 1.0000 0.0228
-8.000 -0.8763 0.01194 0.00630 -0.0042 1.0000 0.0241
-7.750 -0.8523 0.01161 0.00594 -0.0035 1.0000 0.0255
-7.500 -0.8281 0.01132 0.00561 -0.0028 1.0000 0.0265
-7.250 -0.8056 0.01080 0.00507 -0.0017 1.0000 0.0302
-7.000 -0.7820 0.01047 0.00475 -0.0009 1.0000 0.0338
-6.750 -0.7588 0.01010 0.00440 0.0000 1.0000 0.0395
-6.500 -0.7348 0.00984 0.00415 0.0009 1.0000 0.0444
-6.250 -0.7116 0.00951 0.00385 0.0018 1.0000 0.0516
-6.000 -0.6876 0.00931 0.00364 0.0026 1.0000 0.0561
-5.750 -0.6645 0.00900 0.00339 0.0036 1.0000 0.0646
-5.500 -0.6410 0.00878 0.00318 0.0045 1.0000 0.0718
-5.250 -0.6179 0.00854 0.00297 0.0054 1.0000 0.0806
-5.000 -0.5950 0.00829 0.00278 0.0064 1.0000 0.0921
-4.750 -0.5683 0.00806 0.00261 0.0066 0.9994 0.1051
-4.250 -0.4950 0.00754 0.00228 0.0026 0.9943 0.1453
-4.000 -0.4597 0.00725 0.00212 0.0010 0.9906 0.1740
-3.750 -0.4240 0.00699 0.00197 -0.0008 0.9867 0.2004
-3.500 -0.3873 0.00675 0.00184 -0.0027 0.9836 0.2265
-3.250 -0.3546 0.00653 0.00171 -0.0037 0.9772 0.2525
-3.000 -0.3207 0.00628 0.00159 -0.0050 0.9695 0.2843
-2.750 -0.2902 0.00606 0.00147 -0.0054 0.9560 0.3147
-2.500 -0.2612 0.00588 0.00137 -0.0055 0.9377 0.3434
-2.250 -0.2346 0.00573 0.00127 -0.0050 0.9151 0.3724
-2.000 -0.2091 0.00557 0.00118 -0.0043 0.8921 0.4116
-1.750 -0.1836 0.00544 0.00110 -0.0036 0.8690 0.4497
-1.500 -0.1575 0.00535 0.00105 -0.0030 0.8461 0.4816
-1.250 -0.1315 0.00528 0.00099 -0.0025 0.8208 0.5132
-1.000 -0.1054 0.00521 0.00095 -0.0019 0.7939 0.5475
-0.750 -0.0791 0.00516 0.00091 -0.0014 0.7668 0.5801
-0.500 -0.0526 0.00511 0.00089 -0.0010 0.7409 0.6151
-0.250 -0.0263 0.00505 0.00088 -0.0005 0.7149 0.6517
0.000 0.0000 0.00503 0.00087 0.0000 0.6853 0.6853
0.250 0.0263 0.00505 0.00088 0.0005 0.6518 0.7150
0.500 0.0526 0.00511 0.00089 0.0010 0.6151 0.7408
0.750 0.0791 0.00516 0.00091 0.0014 0.5798 0.7667
1.000 0.1054 0.00521 0.00095 0.0019 0.5475 0.7939
1.250 0.1314 0.00528 0.00099 0.0025 0.5128 0.8210
1.500 0.1575 0.00535 0.00105 0.0030 0.4816 0.8461
1.750 0.1836 0.00544 0.00110 0.0036 0.4500 0.8690
2.000 0.2091 0.00558 0.00118 0.0043 0.4112 0.8919
2.250 0.2346 0.00573 0.00127 0.0050 0.3725 0.9151
2.500 0.2612 0.00588 0.00137 0.0055 0.3433 0.9377
2.750 0.2902 0.00606 0.00147 0.0054 0.3149 0.9559
3.000 0.3207 0.00628 0.00159 0.0050 0.2844 0.9695
3.250 0.3546 0.00653 0.00172 0.0037 0.2524 0.9771
3.500 0.3873 0.00675 0.00184 0.0027 0.2265 0.9836
3.750 0.4239 0.00699 0.00197 0.0008 0.2005 0.9866
4.000 0.4596 0.00725 0.00212 -0.0010 0.1741 0.9906
4.250 0.4948 0.00754 0.00228 -0.0026 0.1457 0.9943
4.750 0.5681 0.00806 0.00261 -0.0066 0.1051 0.9993
5.000 0.5953 0.00829 0.00278 -0.0065 0.0921 1.0000
5.250 0.6182 0.00854 0.00297 -0.0055 0.0806 1.0000
5.500 0.6413 0.00878 0.00318 -0.0045 0.0717 1.0000
5.750 0.6648 0.00900 0.00339 -0.0036 0.0645 1.0000
6.000 0.6879 0.00931 0.00364 -0.0027 0.0561 1.0000
6.250 0.7118 0.00951 0.00385 -0.0018 0.0516 1.0000
6.500 0.7351 0.00984 0.00415 -0.0009 0.0444 1.0000
6.750 0.7590 0.01010 0.00440 -0.0001 0.0394 1.0000
7.000 0.7823 0.01047 0.00475 0.0008 0.0337 1.0000
7.250 0.8058 0.01080 0.00507 0.0017 0.0302 1.0000
7.500 0.8282 0.01132 0.00561 0.0027 0.0265 1.0000
7.750 0.8523 0.01161 0.00594 0.0035 0.0255 1.0000
8.000 0.8763 0.01194 0.00630 0.0042 0.0241 1.0000
8.250 0.9000 0.01234 0.00671 0.0049 0.0228 1.0000
8.500 0.9227 0.01290 0.00730 0.0058 0.0211 1.0000
8.750 0.9444 0.01360 0.00809 0.0068 0.0199 1.0000
9.000 0.9689 0.01390 0.00843 0.0074 0.0194 1.0000
9.250 0.9929 0.01429 0.00887 0.0080 0.0187 1.0000
9.500 1.0164 0.01472 0.00935 0.0086 0.0179 1.0000
9.750 1.0397 0.01518 0.00985 0.0093 0.0172 1.0000
10.000 1.0623 0.01572 0.01041 0.0100 0.0163 1.0000
10.250 1.0800 0.01687 0.01166 0.0113 0.0151 1.0000
10.500 1.1024 0.01738 0.01224 0.0120 0.0147 1.0000
10.750 1.1258 0.01776 0.01268 0.0126 0.0142 1.0000
11.000 1.1481 0.01825 0.01323 0.0133 0.0137 1.0000
11.250 1.1701 0.01876 0.01379 0.0140 0.0131 1.0000
11.500 1.1919 0.01924 0.01431 0.0147 0.0124 1.0000
11.750 1.2118 0.01992 0.01501 0.0156 0.0117 1.0000
12.000 1.2229 0.02144 0.01667 0.0174 0.0109 1.0000
12.250 1.2453 0.02177 0.01704 0.0181 0.0106 1.0000
12.500 1.2654 0.02229 0.01765 0.0189 0.0101 1.0000
12.750 1.2845 0.02288 0.01828 0.0199 0.0096 1.0000
13.000 1.3025 0.02350 0.01896 0.0209 0.0092 1.0000
13.250 1.3184 0.02425 0.01975 0.0221 0.0087 1.0000
13.500 1.3290 0.02532 0.02088 0.0239 0.0083 1.0000
13.750 1.3198 0.02717 0.02288 0.0280 0.0078 1.0000
14.000 1.3241 0.02832 0.02413 0.0302 0.0077 1.0000
14.250 1.3311 0.02940 0.02530 0.0317 0.0075 1.0000
14.500 1.3312 0.03109 0.02710 0.0332 0.0074 1.0000
14.750 1.3292 0.03321 0.02934 0.0341 0.0073 1.0000
15.000 1.3291 0.03546 0.03170 0.0342 0.0071 1.0000
15.250 1.3258 0.03836 0.03472 0.0336 0.0069 1.0000
15.500 1.3192 0.04210 0.03858 0.0320 0.0067 1.0000
15.750 1.3036 0.04766 0.04430 0.0288 0.0067 1.0000
16.000 1.2874 0.05394 0.05074 0.0248 0.0066 1.0000
16.250 1.2686 0.06109 0.05803 0.0202 0.0065 1.0000
16.500 1.2223 0.07324 0.07039 0.0126 0.0068 1.0000
16.750 1.1724 0.08625 0.08360 0.0047 0.0071 1.0000
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Polar data table (+)
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