US1000ROOT (us1000root-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: US1000ROOT (us1000root-il) Reynolds number: 1,000,000 Max Cl/Cd: 52.28 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-us1000root-il-1000000.txt Download as CSV file: xf-us1000root-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: US1000ROOT
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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.9426 0.08384 0.07967 -0.0184 1.0000 0.0025
-15.500 -0.9491 0.07959 0.07536 -0.0198 1.0000 0.0026
-15.250 -0.9616 0.07459 0.07027 -0.0213 1.0000 0.0025
-15.000 -0.9703 0.07011 0.06571 -0.0227 1.0000 0.0025
-14.750 -0.9860 0.06482 0.06032 -0.0242 1.0000 0.0025
-14.500 -0.9916 0.06089 0.05632 -0.0254 1.0000 0.0025
-14.250 -1.0125 0.05514 0.05044 -0.0270 1.0000 0.0026
-14.000 -1.0031 0.05318 0.04845 -0.0275 1.0000 0.0025
-13.750 -1.0043 0.04995 0.04516 -0.0283 1.0000 0.0025
-13.500 -1.0163 0.04557 0.04067 -0.0293 1.0000 0.0025
-13.250 -1.0361 0.04043 0.03538 -0.0303 1.0000 0.0025
-13.000 -1.0430 0.03696 0.03181 -0.0306 1.0000 0.0025
-12.750 -1.0355 0.03514 0.02995 -0.0307 1.0000 0.0026
-12.500 -1.0528 0.03107 0.02571 -0.0303 1.0000 0.0026
-12.250 -1.0473 0.02933 0.02393 -0.0297 1.0000 0.0026
-12.000 -1.0502 0.02704 0.02152 -0.0286 1.0000 0.0026
-11.750 -1.0498 0.02519 0.01959 -0.0272 1.0000 0.0026
-11.500 -1.0485 0.02357 0.01789 -0.0254 1.0000 0.0027
-11.250 -1.0440 0.02229 0.01655 -0.0236 1.0000 0.0028
-11.000 -1.0384 0.02119 0.01540 -0.0216 1.0000 0.0028
-10.750 -1.0338 0.02016 0.01431 -0.0192 1.0000 0.0029
-10.500 -1.0297 0.01925 0.01335 -0.0163 1.0000 0.0031
-10.250 -1.0237 0.01855 0.01259 -0.0133 1.0000 0.0030
-10.000 -1.0163 0.01802 0.01203 -0.0102 1.0000 0.0031
-9.750 -0.9792 0.01731 0.01129 -0.0132 0.9973 0.0033
-9.500 -0.9616 0.01649 0.01041 -0.0120 0.9509 0.0035
-9.250 -0.9116 0.01573 0.00959 -0.0175 0.9406 0.0037
-9.000 -0.8584 0.01499 0.00879 -0.0236 0.9316 0.0040
-8.750 -0.8032 0.01432 0.00804 -0.0302 0.9195 0.0050
-8.500 -0.7721 0.01164 0.00586 -0.0344 0.9006 0.1136
-8.250 -0.7367 0.01104 0.00534 -0.0369 0.8875 0.1369
-8.000 -0.7205 0.01015 0.00472 -0.0356 0.8744 0.1919
-7.750 -0.6970 0.00988 0.00450 -0.0350 0.8646 0.2099
-7.500 -0.6740 0.00968 0.00430 -0.0343 0.8550 0.2239
-7.250 -0.6547 0.00949 0.00415 -0.0326 0.8453 0.2363
-7.000 -0.6324 0.00942 0.00402 -0.0315 0.8361 0.2385
-6.750 -0.6123 0.00926 0.00387 -0.0300 0.8272 0.2489
-6.500 -0.5913 0.00913 0.00374 -0.0286 0.8177 0.2572
-6.250 -0.5695 0.00902 0.00361 -0.0274 0.8079 0.2637
-6.000 -0.5476 0.00892 0.00349 -0.0262 0.7975 0.2714
-5.750 -0.5260 0.00881 0.00338 -0.0249 0.7862 0.2785
-5.500 -0.5027 0.00875 0.00326 -0.0239 0.7741 0.2822
-5.250 -0.4818 0.00862 0.00312 -0.0224 0.7616 0.2875
-5.000 -0.4597 0.00855 0.00300 -0.0212 0.7467 0.2926
-4.750 -0.4367 0.00850 0.00290 -0.0201 0.7322 0.2976
-4.500 -0.4154 0.00841 0.00277 -0.0187 0.7153 0.3030
-4.250 -0.3927 0.00836 0.00267 -0.0176 0.6988 0.3080
-4.000 -0.3701 0.00833 0.00257 -0.0164 0.6814 0.3130
-3.750 -0.3482 0.00827 0.00248 -0.0152 0.6641 0.3194
-3.500 -0.3250 0.00826 0.00241 -0.0141 0.6450 0.3249
-3.250 -0.3029 0.00821 0.00232 -0.0129 0.6270 0.3314
-3.000 -0.2800 0.00819 0.00226 -0.0118 0.6091 0.3380
-2.750 -0.2577 0.00817 0.00219 -0.0106 0.5907 0.3451
-2.500 -0.2347 0.00817 0.00214 -0.0095 0.5714 0.3525
-2.250 -0.2119 0.00815 0.00209 -0.0085 0.5541 0.3600
-2.000 -0.1886 0.00815 0.00205 -0.0075 0.5382 0.3677
-1.750 -0.1656 0.00813 0.00201 -0.0064 0.5230 0.3756
-1.500 -0.1419 0.00814 0.00198 -0.0055 0.5088 0.3836
-1.250 -0.1189 0.00813 0.00195 -0.0045 0.4952 0.3921
-1.000 -0.0951 0.00814 0.00194 -0.0036 0.4818 0.4004
-0.750 -0.0720 0.00814 0.00192 -0.0025 0.4698 0.4102
-0.500 -0.0486 0.00814 0.00191 -0.0016 0.4588 0.4195
0.000 -0.0008 0.00812 0.00190 0.0002 0.4387 0.4388
0.500 0.0471 0.00814 0.00191 0.0019 0.4193 0.4587
0.750 0.0704 0.00814 0.00192 0.0029 0.4103 0.4701
1.000 0.0936 0.00814 0.00194 0.0039 0.4006 0.4823
1.250 0.1173 0.00813 0.00196 0.0048 0.3921 0.4955
1.500 0.1404 0.00814 0.00199 0.0059 0.3837 0.5088
1.750 0.1641 0.00813 0.00201 0.0068 0.3757 0.5229
2.000 0.1871 0.00815 0.00205 0.0078 0.3679 0.5379
2.250 0.2104 0.00815 0.00209 0.0088 0.3600 0.5541
2.500 0.2331 0.00817 0.00215 0.0099 0.3526 0.5717
2.750 0.2562 0.00818 0.00220 0.0110 0.3449 0.5897
3.000 0.2787 0.00820 0.00226 0.0121 0.3379 0.6080
3.250 0.3013 0.00821 0.00233 0.0133 0.3308 0.6266
3.500 0.3211 0.00835 0.00239 0.0149 0.3037 0.6446
3.750 0.3428 0.00841 0.00247 0.0162 0.2937 0.6645
4.000 0.3651 0.00845 0.00256 0.0174 0.2864 0.6819
4.250 0.3860 0.00857 0.00266 0.0188 0.2713 0.6985
4.500 0.4072 0.00867 0.00277 0.0202 0.2595 0.7155
4.750 0.4238 0.00897 0.00294 0.0224 0.2264 0.7310
5.000 0.4427 0.00917 0.00310 0.0242 0.2074 0.7473
5.500 0.4398 0.01132 0.00446 0.0348 0.0178 0.7741
5.750 0.4569 0.01156 0.00470 0.0370 0.0045 0.7867
6.000 0.4754 0.01170 0.00487 0.0388 0.0045 0.7987
6.250 0.4943 0.01187 0.00509 0.0406 0.0042 0.8096
6.500 0.5141 0.01205 0.00532 0.0421 0.0041 0.8204
6.750 0.5344 0.01227 0.00559 0.0435 0.0040 0.8304
7.000 0.5548 0.01249 0.00586 0.0448 0.0040 0.8406
7.250 0.5782 0.01274 0.00617 0.0455 0.0040 0.8501
7.500 0.6022 0.01301 0.00650 0.0459 0.0040 0.8604
7.750 0.6277 0.01332 0.00687 0.0459 0.0040 0.8714
8.000 0.6596 0.01367 0.00731 0.0445 0.0040 0.8827
8.250 0.6999 0.01404 0.00774 0.0413 0.0040 0.8939
8.500 0.7463 0.01462 0.00844 0.0366 0.0040 0.9073
8.750 0.7970 0.01533 0.00928 0.0308 0.0041 0.9230
9.000 0.8495 0.01625 0.01030 0.0245 0.0042 0.9353
9.250 0.9002 0.01732 0.01147 0.0185 0.0042 0.9450
9.500 0.9192 0.01849 0.01273 0.0188 0.0043 0.9960
9.750 0.9544 0.01957 0.01388 0.0156 0.0044 1.0000
10.000 0.9603 0.02032 0.01467 0.0184 0.0044 1.0000
10.250 0.9651 0.02124 0.01563 0.0210 0.0045 1.0000
10.500 0.9701 0.02230 0.01674 0.0232 0.0045 1.0000
10.750 0.9760 0.02344 0.01793 0.0251 0.0046 1.0000
11.000 0.9800 0.02481 0.01937 0.0268 0.0046 1.0000
11.250 0.9836 0.02637 0.02100 0.0282 0.0048 1.0000
11.500 0.9752 0.02904 0.02383 0.0299 0.0052 1.0000
11.750 0.9756 0.03122 0.02608 0.0306 0.0052 1.0000
12.000 0.9723 0.03391 0.02887 0.0310 0.0053 1.0000
12.250 0.9678 0.03692 0.03197 0.0311 0.0054 1.0000
12.500 0.9555 0.04087 0.03603 0.0309 0.0056 1.0000
12.750 0.9218 0.04671 0.04196 0.0312 0.0062 1.0000
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Polar data table (+)
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