AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AQUILA 9.3% smoothed (aquilasm-il) Reynolds number: 500,000 Max Cl/Cd: 104.76 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-aquilasm-il-500000.txt Download as CSV file: xf-aquilasm-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AQUILA 9.3% smoothed
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3083 0.08600 0.08388 -0.0300 1.0000 0.0154
-7.750 -0.3078 0.08343 0.08135 -0.0303 1.0000 0.0159
-7.500 -0.3106 0.08100 0.07897 -0.0302 1.0000 0.0161
-7.250 -0.3184 0.07887 0.07692 -0.0296 0.9993 0.0163
-7.000 -0.2933 0.07370 0.07173 -0.0385 0.9850 0.0168
-6.750 -0.2526 0.06635 0.06429 -0.0553 0.9717 0.0183
-6.500 -0.2156 0.06034 0.05813 -0.0658 0.9581 0.0185
-6.250 -0.1845 0.05515 0.05279 -0.0725 0.9419 0.0186
-6.000 -0.1715 0.04953 0.04705 -0.0754 0.9204 0.0190
-5.750 -0.1561 0.04675 0.04414 -0.0761 0.9007 0.0193
-5.500 -0.1402 0.04429 0.04155 -0.0764 0.8826 0.0196
-5.250 -0.1233 0.04177 0.03887 -0.0766 0.8657 0.0201
-5.000 -0.1049 0.03915 0.03608 -0.0768 0.8501 0.0207
-4.750 -0.0850 0.03645 0.03316 -0.0768 0.8356 0.0218
-4.500 -0.0566 0.03409 0.03040 -0.0761 0.8227 0.0240
-4.250 -0.0340 0.03192 0.02787 -0.0753 0.8096 0.0243
-4.000 -0.0200 0.02717 0.02295 -0.0753 0.7973 0.0254
-3.750 0.0019 0.02568 0.02133 -0.0750 0.7850 0.0264
-3.500 0.0252 0.02413 0.01958 -0.0744 0.7733 0.0277
-3.250 0.0541 0.02403 0.01913 -0.0733 0.7619 0.0316
-3.000 0.0746 0.02045 0.01516 -0.0725 0.7511 0.0333
-2.750 0.0988 0.01912 0.01374 -0.0722 0.7397 0.0346
-2.500 0.1240 0.01805 0.01249 -0.0716 0.7287 0.0364
-2.250 0.1503 0.01713 0.01133 -0.0709 0.7183 0.0390
-2.000 0.1786 0.01339 0.00691 -0.0688 0.7087 0.0237
-1.750 0.2051 0.01244 0.00578 -0.0682 0.6982 0.0239
-1.500 0.2312 0.01156 0.00473 -0.0675 0.6879 0.0246
-1.250 0.2566 0.01081 0.00394 -0.0670 0.6774 0.0267
-1.000 0.2829 0.01044 0.00354 -0.0665 0.6668 0.0286
-0.750 0.3090 0.01008 0.00310 -0.0660 0.6567 0.0304
-0.250 0.3611 0.00945 0.00236 -0.0650 0.6359 0.0393
0.000 0.3874 0.00922 0.00208 -0.0646 0.6258 0.0479
0.250 0.4138 0.00907 0.00190 -0.0642 0.6159 0.0654
0.500 0.4213 0.00681 0.00194 -0.0606 0.6069 0.8268
0.750 0.5071 0.00667 0.00186 -0.0728 0.5931 1.0000
1.000 0.5319 0.00676 0.00184 -0.0721 0.5829 1.0000
1.250 0.5567 0.00687 0.00184 -0.0714 0.5727 1.0000
1.500 0.5818 0.00695 0.00185 -0.0708 0.5620 1.0000
1.750 0.6069 0.00705 0.00188 -0.0702 0.5516 1.0000
2.000 0.6319 0.00716 0.00191 -0.0696 0.5413 1.0000
2.250 0.6569 0.00728 0.00195 -0.0690 0.5305 1.0000
2.500 0.6821 0.00739 0.00201 -0.0684 0.5196 1.0000
2.750 0.7072 0.00751 0.00208 -0.0678 0.5089 1.0000
3.000 0.7321 0.00765 0.00215 -0.0672 0.4982 1.0000
3.250 0.7571 0.00779 0.00223 -0.0667 0.4869 1.0000
3.500 0.7824 0.00792 0.00234 -0.0661 0.4757 1.0000
3.750 0.8075 0.00807 0.00244 -0.0656 0.4643 1.0000
4.000 0.8324 0.00823 0.00256 -0.0651 0.4527 1.0000
4.250 0.8573 0.00841 0.00268 -0.0645 0.4409 1.0000
4.500 0.8823 0.00859 0.00283 -0.0640 0.4288 1.0000
4.750 0.9073 0.00876 0.00298 -0.0635 0.4169 1.0000
5.000 0.9322 0.00895 0.00314 -0.0630 0.4048 1.0000
5.250 0.9570 0.00915 0.00331 -0.0625 0.3926 1.0000
5.500 0.9816 0.00937 0.00351 -0.0620 0.3805 1.0000
5.750 1.0059 0.00961 0.00372 -0.0614 0.3684 1.0000
6.000 1.0304 0.00985 0.00393 -0.0609 0.3564 1.0000
6.250 1.0549 0.01008 0.00415 -0.0604 0.3442 1.0000
6.500 1.0792 0.01033 0.00441 -0.0598 0.3324 1.0000
6.750 1.1032 0.01060 0.00466 -0.0593 0.3208 1.0000
7.000 1.1268 0.01089 0.00493 -0.0587 0.3074 1.0000
7.250 1.1501 0.01120 0.00522 -0.0580 0.2916 1.0000
7.500 1.1733 0.01152 0.00551 -0.0574 0.2784 1.0000
7.750 1.1964 0.01185 0.00583 -0.0567 0.2668 1.0000
8.250 1.2415 0.01256 0.00653 -0.0553 0.2418 1.0000
8.500 1.2633 0.01295 0.00690 -0.0545 0.2266 1.0000
8.750 1.2848 0.01336 0.00729 -0.0537 0.2090 1.0000
9.000 1.3053 0.01384 0.00772 -0.0527 0.1912 1.0000
9.250 1.3240 0.01443 0.00824 -0.0515 0.1702 1.0000
9.500 1.3414 0.01510 0.00880 -0.0502 0.1471 1.0000
9.750 1.3575 0.01583 0.00945 -0.0486 0.1239 1.0000
10.000 1.3707 0.01673 0.01021 -0.0467 0.0992 1.0000
10.250 1.3816 0.01772 0.01108 -0.0445 0.0768 1.0000
10.500 1.3896 0.01875 0.01202 -0.0418 0.0593 1.0000
10.750 1.3963 0.01967 0.01291 -0.0389 0.0475 1.0000
11.000 1.4014 0.02071 0.01392 -0.0359 0.0369 1.0000
11.250 1.4037 0.02197 0.01515 -0.0328 0.0266 1.0000
11.500 1.4050 0.02339 0.01656 -0.0299 0.0198 1.0000
11.750 1.4054 0.02500 0.01822 -0.0273 0.0157 1.0000
12.000 1.4075 0.02661 0.01989 -0.0252 0.0140 1.0000
12.250 1.4054 0.02868 0.02207 -0.0232 0.0128 1.0000
12.500 1.4084 0.03049 0.02399 -0.0218 0.0123 1.0000
12.750 1.4100 0.03253 0.02616 -0.0207 0.0117 1.0000
13.000 1.4093 0.03491 0.02865 -0.0198 0.0111 1.0000
13.250 1.4091 0.03739 0.03123 -0.0191 0.0108 1.0000
13.500 1.4055 0.04033 0.03429 -0.0187 0.0105 1.0000
13.750 1.3963 0.04408 0.03814 -0.0186 0.0100 1.0000
14.000 1.3864 0.04805 0.04224 -0.0188 0.0098 1.0000
14.250 1.3766 0.05218 0.04649 -0.0192 0.0097 1.0000
14.500 1.3649 0.05668 0.05112 -0.0199 0.0095 1.0000
14.750 1.3604 0.06045 0.05501 -0.0206 0.0094 1.0000
15.000 1.3564 0.06428 0.05896 -0.0215 0.0092 1.0000
15.250 1.3501 0.06849 0.06329 -0.0226 0.0092 1.0000
15.500 1.3453 0.07264 0.06755 -0.0238 0.0090 1.0000
15.750 1.3384 0.07720 0.07222 -0.0251 0.0087 1.0000
16.000 1.3335 0.08153 0.07666 -0.0266 0.0086 1.0000
16.250 1.3266 0.08624 0.08148 -0.0281 0.0084 1.0000
16.500 1.3208 0.09086 0.08621 -0.0297 0.0084 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AQUILA 9.3% smoothed (aquilasm-il)