S9000 (9%) (s9000-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9000 (9%) (s9000-il) Reynolds number: 500,000 Max Cl/Cd: 92.99 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9000-il-500000.txt Download as CSV file: xf-s9000-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S9000 (9%)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4407 0.08732 0.08507 -0.0300 1.0000 0.0162
-8.750 -0.4409 0.08411 0.08189 -0.0305 1.0000 0.0164
-8.500 -0.4416 0.08105 0.07886 -0.0311 1.0000 0.0166
-8.250 -0.4446 0.07778 0.07563 -0.0318 1.0000 0.0168
-8.000 -0.4511 0.07455 0.07244 -0.0322 1.0000 0.0170
-7.750 -0.4643 0.07116 0.06911 -0.0326 1.0000 0.0170
-7.500 -0.4722 0.06570 0.06367 -0.0375 1.0000 0.0170
-7.250 -0.4767 0.06106 0.05900 -0.0399 1.0000 0.0172
-7.000 -0.4801 0.05659 0.05448 -0.0411 1.0000 0.0173
-6.750 -0.4815 0.05265 0.05046 -0.0413 1.0000 0.0176
-6.500 -0.4803 0.04880 0.04650 -0.0413 0.9999 0.0180
-6.250 -0.4506 0.04274 0.04017 -0.0474 0.9966 0.0190
-6.000 -0.4168 0.03712 0.03412 -0.0521 0.9936 0.0212
-5.750 -0.3809 0.03508 0.03157 -0.0547 0.9897 0.0222
-5.500 -0.3570 0.02046 0.01559 -0.0574 0.9861 0.0113
-5.250 -0.3222 0.01760 0.01243 -0.0593 0.9843 0.0103
-5.000 -0.2899 0.01527 0.00975 -0.0602 0.9809 0.0098
-4.750 -0.2569 0.01374 0.00802 -0.0612 0.9770 0.0096
-4.500 -0.2214 0.01256 0.00670 -0.0627 0.9741 0.0098
-4.250 -0.1843 0.01165 0.00568 -0.0646 0.9718 0.0105
-4.000 -0.1509 0.01072 0.00465 -0.0658 0.9676 0.0121
-3.750 -0.1167 0.01003 0.00393 -0.0670 0.9627 0.0183
-3.500 -0.0789 0.00936 0.00338 -0.0691 0.9595 0.0455
-3.250 -0.0408 0.00874 0.00300 -0.0715 0.9570 0.0995
-3.000 -0.0118 0.00817 0.00272 -0.0718 0.9484 0.1749
-2.750 0.0235 0.00763 0.00246 -0.0735 0.9437 0.2605
-2.500 0.0532 0.00718 0.00227 -0.0740 0.9342 0.3442
-2.250 0.0854 0.00674 0.00208 -0.0750 0.9256 0.4346
-2.000 0.1167 0.00627 0.00193 -0.0757 0.9152 0.5398
-1.750 0.1449 0.00590 0.00185 -0.0756 0.9014 0.6425
-1.500 0.1723 0.00574 0.00181 -0.0751 0.8864 0.7114
-1.250 0.1989 0.00566 0.00179 -0.0744 0.8708 0.7587
-1.000 0.2250 0.00563 0.00177 -0.0737 0.8546 0.7918
-0.750 0.2507 0.00563 0.00175 -0.0728 0.8377 0.8195
-0.500 0.2763 0.00565 0.00173 -0.0720 0.8203 0.8430
-0.250 0.3010 0.00568 0.00171 -0.0709 0.8022 0.8631
0.000 0.3254 0.00571 0.00170 -0.0698 0.7832 0.8827
0.250 0.3489 0.00575 0.00169 -0.0685 0.7642 0.9028
0.500 0.3716 0.00578 0.00168 -0.0670 0.7458 0.9226
1.000 0.4233 0.00586 0.00163 -0.0655 0.7063 0.9641
1.500 0.4941 0.00606 0.00160 -0.0686 0.6575 1.0000
1.750 0.5193 0.00620 0.00163 -0.0682 0.6335 1.0000
2.000 0.5452 0.00636 0.00169 -0.0678 0.6105 1.0000
2.250 0.5713 0.00653 0.00175 -0.0675 0.5878 1.0000
2.500 0.5975 0.00671 0.00183 -0.0672 0.5637 1.0000
2.750 0.6237 0.00690 0.00192 -0.0669 0.5394 1.0000
3.000 0.6497 0.00712 0.00204 -0.0665 0.5142 1.0000
3.250 0.6755 0.00735 0.00216 -0.0662 0.4851 1.0000
3.500 0.7013 0.00761 0.00229 -0.0658 0.4567 1.0000
3.750 0.7273 0.00784 0.00244 -0.0655 0.4310 1.0000
4.000 0.7532 0.00810 0.00262 -0.0652 0.4045 1.0000
4.250 0.7789 0.00838 0.00280 -0.0648 0.3778 1.0000
4.500 0.8046 0.00867 0.00300 -0.0645 0.3538 1.0000
4.750 0.8301 0.00898 0.00322 -0.0642 0.3277 1.0000
5.000 0.8551 0.00934 0.00346 -0.0638 0.2961 1.0000
5.250 0.8801 0.00971 0.00371 -0.0634 0.2687 1.0000
5.500 0.9052 0.01007 0.00398 -0.0630 0.2452 1.0000
5.750 0.9305 0.01041 0.00428 -0.0626 0.2235 1.0000
6.250 0.9802 0.01118 0.00492 -0.0618 0.1829 1.0000
6.500 1.0045 0.01162 0.00528 -0.0613 0.1623 1.0000
6.750 1.0288 0.01205 0.00566 -0.0609 0.1433 1.0000
7.000 1.0528 0.01251 0.00608 -0.0604 0.1257 1.0000
7.250 1.0760 0.01305 0.00653 -0.0597 0.1071 1.0000
7.500 1.0996 0.01355 0.00699 -0.0592 0.0910 1.0000
7.750 1.1226 0.01410 0.00749 -0.0585 0.0770 1.0000
8.000 1.1453 0.01467 0.00804 -0.0578 0.0658 1.0000
8.250 1.1672 0.01531 0.00867 -0.0570 0.0563 1.0000
8.500 1.1901 0.01582 0.00921 -0.0564 0.0497 1.0000
8.750 1.2119 0.01643 0.00985 -0.0555 0.0434 1.0000
9.000 1.2326 0.01715 0.01056 -0.0546 0.0366 1.0000
9.250 1.2541 0.01774 0.01123 -0.0537 0.0314 1.0000
9.500 1.2713 0.01878 0.01229 -0.0523 0.0255 1.0000
9.750 1.2922 0.01939 0.01297 -0.0513 0.0216 1.0000
10.000 1.3077 0.02049 0.01413 -0.0497 0.0181 1.0000
10.250 1.3283 0.02104 0.01473 -0.0488 0.0157 1.0000
10.500 1.3413 0.02225 0.01599 -0.0469 0.0133 1.0000
10.750 1.3588 0.02299 0.01682 -0.0456 0.0120 1.0000
11.000 1.3743 0.02383 0.01775 -0.0441 0.0107 1.0000
11.250 1.3834 0.02498 0.01897 -0.0417 0.0096 1.0000
11.500 1.3833 0.02661 0.02074 -0.0381 0.0087 1.0000
11.750 1.3930 0.02761 0.02187 -0.0359 0.0080 1.0000
12.000 1.4003 0.02878 0.02316 -0.0336 0.0072 1.0000
12.250 1.4027 0.03034 0.02482 -0.0312 0.0065 1.0000
12.500 1.3892 0.03326 0.02789 -0.0279 0.0059 1.0000
12.750 1.3896 0.03529 0.03008 -0.0262 0.0057 1.0000
13.000 1.3921 0.03728 0.03223 -0.0250 0.0049 1.0000
13.250 1.3888 0.03998 0.03506 -0.0241 0.0048 1.0000
13.500 1.3857 0.04286 0.03807 -0.0237 0.0045 1.0000
13.750 1.3795 0.04636 0.04170 -0.0239 0.0042 1.0000
14.000 1.3701 0.05059 0.04608 -0.0247 0.0042 1.0000
14.250 1.3543 0.05607 0.05173 -0.0264 0.0040 1.0000
14.500 1.3427 0.06137 0.05719 -0.0285 0.0040 1.0000
14.750 1.3158 0.06945 0.06547 -0.0321 0.0038 1.0000
15.000 1.3098 0.07454 0.07069 -0.0347 0.0039 1.0000
15.250 1.2885 0.08249 0.07883 -0.0387 0.0038 1.0000
15.500 1.2701 0.09030 0.08680 -0.0429 0.0038 1.0000
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Polar data table (+)
Polar graphs
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